Product overview
The MUGINUAV Mugin GV360 Flight Platform is a complete aircraft for professional UAV operations and research projects. Its carbon fiber composite airframe combines electric lift motors for vertical takeoff and landing with a separate gasoline engine for fixed-wing cruise, enabling runway-free deployment. Overall reference dimensions are approximately 3600 × 2420 × 850 mm, with a wing area of 132 dm². The current configuration incorporates upgraded landing gear and VTOL motor mounts, and integrates propulsion, flight control, power and actuation systems.
Inside the fuselage, approximate reference dimensions of 1255 × 262 × 293 mm provide space for flight systems and mission equipment. Installed systems, equipment placement and mounting requirements determine how much room remains for the payload. Payload equipment, communications and ground control equipment are chosen for the individual project; the quotation establishes the final equipment list. Communication reach depends on the chosen data link. Maximum payload is 6 kg, and payload and fuel must be allocated together within the 40 kg maximum take-off weight.
The reference fuel tank holds 10 L. With a 2 kg payload and 10 L of fuel, reference endurance reaches up to four hours. Other reference combinations provide three hours with a 4 kg payload and 7.4 L of fuel, or two hours with a 6 kg payload and 4.8 L. Maximum speed is 35 m/s, cruise speed is 30–32 m/s, and stall speed is 24 m/s. Reference range is 400 km. Performance varies with aircraft configuration, payload, fuel load and operating conditions.
Specifications
| Specification | Value & conditions |
|---|---|
| Manufacturer and model | MUGINUAV Mugin GV360 Flight Platform |
| Supplied configuration | Complete 3.6 m VTOL aircraft for professional UAV operations and research projects |
| Dimensions | Approx. 3600 × 2420 × 850 mmReference dimensions. |
| Fuselage internal dimensions | Approx. 1255 × 262 × 293 mmReference dimensions; usable internal space depends on installed flight systems and equipment layout. |
| Wing area | 132 dm² |
| Primary structure | Carbon fiber composite |
| Propulsion architecture | Gasoline engine for fixed-wing cruise; electric lift motors for vertical takeoff and landing |
| Fuel tank capacity | 10 LReference configuration. |
| Maximum take-off weight | 40 kg |
| Maximum payload | 6 kg |
| Maximum speed | 35 m/sAircraft configuration, payload, fuel load and operating conditions. |
| Cruise speed | 30–32 m/sAircraft configuration, payload, fuel load and operating conditions. |
| Stall speed | 24 m/sAircraft configuration, payload, fuel load and operating conditions. |
| Endurance | Up to 4 hours (reference)2 kg payload and 10 L fuel; final configuration and operating conditions affect actual endurance. |
| Flight range | 400 km (reference)Reference value; aircraft configuration, payload, fuel load and operating conditions. |
| Wind resistance | VTOL Level 4 / Fixed-wing Level 6VTOL or fixed-wing flight mode; aircraft configuration, payload, fuel load and operating conditions. |
| Reference endurance with 4 kg payload | 3 hours4 kg payload; 7.4 L fuel in a 10 L tank; final configuration and operating conditions affect actual endurance. |
| Reference endurance with maximum payload | 2 hours6 kg payload; 4.8 L fuel in a 10 L tank; final configuration and operating conditions affect actual endurance. |
| Integrated systems | Propulsion, flight control, power and actuation systems |
| Mission and ground equipment | Project-selected mission payloads, communication links and ground control equipmentProject-specific selection; final equipment list defined in the quotation. |
| Usable integration space | Internal space accommodates flight systems and project equipment; available mission-payload space depends on layout and mounting requirementsInstalled flight systems, equipment layout and mounting requirements. |
| Landing gear and VTOL motor mounts | Upgraded landing gear and VTOL motor mountsCurrent version. |
| Communication range | Depends on the selected data linkSelected data link. |
| Payload and fuel allocation | Payload and fuel are allocated together to meet endurance requirements within the take-off weight limitAircraft take-off weight limit. |
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