Product overview
The Mugin GF260 Flight Platform gives payload developers a small gasoline-powered fixed-wing aircraft with integrated propulsion, flight control, electrical power and actuation systems. Its fiberglass composite airframe has twin booms supporting an H-tail and a pusher propeller behind the fuselage, leaving the nose free of a propulsion unit. Wheeled landing gear supports conventional runway operation. Reference takeoff and landing distances are 60 m and 180 m respectively; runway planning must account for aircraft loading, surface conditions, weather and operating margins.
Overall dimensions are approximately 2600 × 2050 × 701 mm, with approximate fuselage internal dimensions of 1017 × 221 × 216 mm. A removable upper hatch provides installation and servicing access. Usable space depends on the installed flight systems and equipment layout, so payload dimensions, mounting requirements and placement need to be considered together. The GF260 is supplied as an integrated Flight Platform. Mission payloads, communication links and ground control equipment are selected for each project, with the final equipment list defined in the quotation. Communication range depends on the chosen data link.
Maximum takeoff weight is 16 kg, including aircraft, payload, battery and fuel. The 3 kg maximum payload and longest endurance represent different loading cases: 3 kg of payload with 1.6 L of fuel gives approximately two hours, while 2 kg with 3 L gives approximately 3.5 hours. These endurance references use a DLE40 carbureted gasoline engine; actual endurance depends on engine configuration, aircraft loading and operating conditions. The calculated 302 km reference range corresponds to 2 kg payload and 3 L fuel, with performance dependent on aircraft configuration and operating conditions.
Specifications
| Specification | Value & conditions |
|---|---|
| Product | Mugin GF260 Flight Platform; small gasoline-powered fixed-wing UAV |
| Airframe layout | Twin-boom H-tail with rear-mounted pusher propeller |
| Supplied flight systems | Integrated propulsion, flight control, electrical power and actuation systems |
| Mission equipment | Project-selected mission payloads, communication links and ground control equipmentProject-specific selection; final equipment list defined in the quotation. |
| Dimensions | Approx. 2600 × 2050 × 701 mmFlight Platform reference configuration; reference dimensions. |
| Fuselage internal dimensions | Approx. 1017 × 221 × 216 mmReference dimensions; usable internal space depends on installed flight systems and equipment layout. |
| Wing area | 92 dm²Flight Platform reference configuration. |
| Primary structure | Fiberglass compositeFlight Platform reference configuration. |
| Propulsion | GasolineFlight Platform reference configuration. |
| Fuel tank capacity | 3 L (reference configuration)Reference configuration. |
| Maximum takeoff weight | 16 kgReference configuration; includes aircraft, payload, battery and fuel. |
| Maximum payload | 3 kgReference configuration; maximum payload and maximum endurance refer to different loading cases. |
| Maximum speed | 30 m/sReference configuration; airspeed; performance depends on aircraft configuration and operating conditions. |
| Cruise speed | 24–26 m/sReference configuration; airspeed; performance depends on aircraft configuration and operating conditions. |
| Stall speed | 16 m/sReference configuration; airspeed; performance depends on aircraft configuration and operating conditions. |
| Endurance | Up to 3.5 hours (reference)Reference configuration with 2 kg payload and 3 L fuel; DLE40 carbureted gasoline engine; actual endurance depends on engine configuration, aircraft loading and operating conditions. |
| Flight range | 302 km (reference)Calculated reference range with 2 kg payload and 3 L fuel; performance depends on aircraft configuration and operating conditions. |
| Wind resistance | VTOL: N/A / Fixed-wing: Level 6Flight Platform reference configuration. |
| Takeoff distance | 60 mReference distance; runway planning must account for aircraft loading, surface conditions, weather and operating margins. |
| Landing distance | 180 mReference distance; runway planning must account for aircraft loading, surface conditions, weather and operating margins. |
| Endurance at maximum payload | Approx. 2 Hours3 kg payload and 1.6 L fuel; DLE40 carbureted gasoline engine; actual endurance depends on engine configuration, aircraft loading and operating conditions. |
| Endurance with 3 L fuel | Approx. 3.5 Hours2 kg payload and 3 L fuel; DLE40 carbureted gasoline engine; actual endurance depends on engine configuration, aircraft loading and operating conditions. |
| Equipment access | Removable upper hatch for equipment installation and servicing |
| Takeoff and landing architecture | Conventional runway takeoff and landing on wheeled landing gear |
| Communication range | Depends on the selected data linkSelected data link. |
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