Product overview
The MUGINUAV Mugin GF600 Flight Platform is a gasoline-powered fixed-wing UAV for long-endurance mapping, surveying and inspection. Its carbon fiber composite airframe combines twin tail booms with reinforced internal ribs; each boom separates into two sections for transport. Conventional runway operation includes disc brakes for landing-roll deceleration. Reference takeoff and landing distances are 200 m and 300 m, with planning dependent on aircraft loading, configuration, surface conditions, weather and operating margins. Overall dimensions are approximately 6000 × 3500 × 960 mm, with a wing area of 312 dm².
The Flight Platform includes propulsion, flight control, electrical power and actuation systems. Its approximately 1800 × 368 × 393 mm fuselage interior accommodates flight systems and mission equipment; usable space depends on their layout. Payload dimensions, mounts, power requirements and wiring need checking against that layout. Mission payloads, communication links and ground control equipment are application-selected, with the final list defined in the quotation. Communication range depends on the selected data link. The separate GF600 Airframe Kit allows customers to integrate their own propulsion and flight-control systems.
Maximum take-off weight is 90 kg, with a 30 L reference fuel tank capacity. Maximum payload of 30 kg, endurance up to 7.5 hours and range of 712 km are separate reference limits and should not be assumed to occur together. Reference endurance calculations using the DLA232 EFI engine give approximately four hours with 30 kg payload and 21 L fuel, or six hours with 23 kg payload and 30 L fuel. Different engine configurations produce different endurance performance; performance also depends on aircraft configuration, payload, fuel load and operating conditions.
Specifications
| Specification | Value & conditions |
|---|---|
| Manufacturer and model | MUGINUAV Mugin GF600 Flight Platform |
| Airframe architecture | Carbon fiber twin-boom airframe with reinforced internal ribs |
| Transport arrangement | Each tail boom separates into two sections |
| Dimensions | Approx. 6000 × 3500 × 960 mmFlight Platform reference configuration; dimensions are reference values. |
| Fuselage internal dimensions | Approx. 1800 × 368 × 393 mmFlight Platform reference configuration; dimensions are reference values. Usable internal space depends on installed flight systems and equipment layout. |
| Wing area | 312 dm²Flight Platform reference configuration. |
| Primary structure | Carbon Fiber CompositeFlight Platform reference configuration. |
| Propulsion | GasolineFlight Platform reference configuration. |
| Fuel tank capacity | 30 LReference configuration. |
| Maximum take-off weight | 90 kgFlight Platform reference configuration. |
| Maximum payload | 30 kgFlight Platform reference configuration; performance depends on aircraft configuration, payload, fuel load and operating conditions. Maximum payload, endurance and range are separate reference limits and should not be assumed to occur together. |
| Maximum speed | 40 m/sFlight Platform reference configuration; performance depends on aircraft configuration, payload, fuel load and operating conditions. |
| Cruise speed | 30–35 m/sFlight Platform reference configuration; performance depends on aircraft configuration, payload, fuel load and operating conditions. |
| Stall speed | 25 m/sFlight Platform reference configuration; performance depends on aircraft configuration, payload, fuel load and operating conditions. |
| Endurance | Up to 7.5 hours (reference)Flight Platform reference configuration; performance depends on aircraft configuration, payload, fuel load and operating conditions. Maximum payload, endurance and range are separate reference limits and should not be assumed to occur together. |
| Flight range | 712 km (reference)Flight Platform reference configuration; performance depends on aircraft configuration, payload, fuel load and operating conditions. Maximum payload, endurance and range are separate reference limits and should not be assumed to occur together. |
| Wind resistance | VTOL: N/A / Fixed-wing: Level 6Flight Platform reference configuration; performance depends on aircraft configuration, payload, fuel load and operating conditions. |
| Takeoff distance | 200 mReference distance; depends on aircraft loading and operating conditions. Runway planning must account for aircraft configuration, surface conditions, weather and operating margins. |
| Landing distance | 300 mReference distance; depends on aircraft loading and operating conditions. Runway planning must account for aircraft configuration, surface conditions, weather and operating margins. |
| Endurance with 30 kg payload | Approx. 4 Hours30 kg payload and 21 L fuel load; calculated using the DLA232 EFI engine. Different engine configurations result in different endurance performance. |
| Endurance with 23 kg payload | Approx. 6 Hours23 kg payload and 30 L fuel load; calculated using the DLA232 EFI engine. Different engine configurations result in different endurance performance. |
| Runway operation and braking | Conventional runway takeoff and landing, with disc brakes for landing-roll deceleration |
| Included aircraft systems | Propulsion, flight control, electrical power and actuation systemsMugin GF600 Flight Platform configuration. |
| Mission and ground equipment | Application-selected mission payloads, communication links and ground control equipmentEquipment selected for the application; final equipment list defined in the quotation. |
| Payload installation checks | Payload dimensions, mounting points, electrical power requirements and wiring should be checked against the final equipment layoutFinal equipment layout. |
| Communication range | Depends on the selected data linkSelected data link. |
| Airframe-only alternative | Separate Mugin GF600 Airframe Kit for customer integration of propulsion and flight-control systemsSeparate Airframe Kit configuration. |
| Purpose | Long-endurance mapping, surveying and inspection |
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