Product overview
The Mugin GF450 Flight Platform carries survey and inspection equipment in a gasoline-powered fixed-wing airframe built primarily from fiberglass composite. Overall dimensions are approximately 4500 × 3500 × 870 mm, with a wing area of 180 dm². Its wheeled landing gear requires runway access for departure and recovery. Maximum takeoff weight is 32 kg, and the mission payload limit is 8 kg. Payload planning includes the cameras or sensors together with their mounting hardware, rather than considering the equipment weight alone.
The Flight Platform configuration includes the airframe and integrated propulsion, flight control, power and actuation systems. Payload hardware, communications and ground control equipment are selected for the individual project; the quotation establishes the equipment supplied. Reference fuselage internal dimensions are approximately 1255 × 262 × 293 mm. Available installation space depends on the systems already fitted, so equipment dimensions, mounting arrangements and power requirements shape the payload layout. These dimensions provide a planning reference rather than a guaranteed clear equipment envelope.
The 10 L tank supports mission-dependent fuel loads. Reference endurance is five hours with an 8 kg payload and 5 L of fuel, or seven hours with a 6 kg payload and 7.5 L, verified using a DLE60 carbureted gasoline engine. Actual endurance depends on loading, engine configuration, flight profile and operating conditions. Maximum payload and maximum endurance therefore represent different configurations. Range is a calculated 604 km reference; the 150 m takeoff and 230 m landing references require allowances for aircraft configuration, runway surface, weather and operating margins.
Specifications
| Specification | Value & conditions |
|---|---|
| Product | Mugin GF450 Flight Platform |
| Overall dimensions | Approx. 4500 × 3500 × 870 mmReference dimensions. |
| Fuselage internal dimensions | Approx. 1255 × 262 × 293 mmReference dimensions; usable installation space depends on fitted systems and equipment. |
| Wing area | 180 dm² |
| Primary structure | Primarily fiberglass composite |
| Propulsion | Gasoline |
| Fuel tank capacity | 10 LFuel load varies with mission configuration. |
| Maximum takeoff weight | 32 kg |
| Maximum payload | 8 kgMaximum payload and maximum endurance apply to different operating conditions. |
| Maximum speed | 35 m/s |
| Cruise speed | 24–26 m/s |
| Stall speed | 19 m/sAt 32 kg maximum takeoff weight. |
| Endurance | Up to 7 hours (reference)Reference with 6 kg payload and 7.5 L fuel; endurance figures verified using a DLE60 carbureted gasoline engine. Actual endurance depends on aircraft loading, engine configuration, flight profile and operating conditions. |
| Flight range | 604 km (reference)Calculated reference. |
| Wind resistance | VTOL: N/A / Fixed-wing: Level 6Fixed-wing operation; VTOL rating is not applicable. |
| Takeoff and landing configuration | Runway takeoff and landing with wheeled landing gear |
| Takeoff distance | 150 mReference distance; runway planning must account for aircraft configuration, surface conditions, weather and operating margins. |
| Landing distance | 230 mReference distance; runway planning must account for aircraft configuration, surface conditions, weather and operating margins. |
| Maximum-payload endurance combination | 8 kg payload / 5 L fuel / 5 hours reference endurance8 kg payload and 5 L fuel; endurance figures verified using a DLE60 carbureted gasoline engine. Actual endurance depends on aircraft loading, engine configuration, flight profile and operating conditions. |
| Longer-endurance combination | 6 kg payload / 7.5 L fuel / 7 hours reference endurance6 kg payload and 7.5 L fuel; endurance figures verified using a DLE60 carbureted gasoline engine. Actual endurance depends on aircraft loading, engine configuration, flight profile and operating conditions. |
| Integrated equipment | Airframe with integrated propulsion, flight control, power and actuation systemsFlight Platform configuration. |
| Mission equipment configuration | Mission payloads, communication links and ground control equipment configured for each projectProject-specific equipment; final equipment list defined in the quotation. |
| Installation space limitation | Reference dimensions do not specify the available equipment installation spaceFitted systems and equipment determine usable installation space. |
| Endurance dependencies | Actual endurance varies with loading, engine configuration, flight profile and operating conditionsAircraft loading, engine configuration, flight profile and operating conditions. |
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