Product overview
The Mugin UAV EV460 serves system integrators requiring an electric VTOL platform with space for payloads and onboard equipment. Its carbon fiber composite structure combines a twin-boom H-tail, three-point skid landing gear and detachable major airframe sections for transport, assembly and maintenance. Dedicated lift motors support vertical takeoff and landing, while a separate electric pusher powers fixed-wing cruise. Overall dimensions are approximately 4600 × 2180 × 698 mm; these are reference values that may vary with platform configuration, antenna installation and integrated equipment.
The fuselage provides approximately 1257 × 295 × 331 mm of internal space for sensors, communications, onboard computing, power distribution and project-specific systems. These internal dimensions are also reference values and may vary with platform configuration, antenna installation and integrated equipment. The EV460 is supplied as a complete flight platform, with propulsion, flight control, power distribution and actuation integrated according to the confirmed configuration. Payloads, data links, communication equipment, ground control equipment and other mission-specific systems are selected according to project requirements.
The current published specifications give a maximum payload of 8 kg and maximum take-off weight of 42 kg. The recommended platform setup uses 2 × 12S 33000 mAh batteries. Listed speeds are 30 m/s maximum, 21-24 m/s cruise and 18 m/s stall. Published endurance is 1.5-2 hours and range is 150 km; actual results vary with payload, battery condition, flight profile, environmental conditions and system configuration. Wind resistance ratings distinguish Level 4 VTOL operation from Level 6 fixed-wing operation.
Specifications
| Specification | Value & conditions |
|---|---|
| Manufacturer and product identity | Mugin UAV EV460; current designation: Mugin EV460 Flight Platform |
| Dimensions | Approx. 4600 × 2180 × 698 mmReference dimensions; actual dimensions may vary depending on platform configuration, antenna installation and integrated equipment. |
| Fuselage Internal Dimensions | Approx. 1257 × 295 × 331 mmReference dimensions; actual dimensions may vary depending on platform configuration, antenna installation and integrated equipment. |
| Wing Area | 160 dm² |
| Primary Structure | Carbon Fiber Composite |
| Propulsion | Full Electric |
| Battery Configuration | 2 × 12S 33000 mAhBattery configuration is based on the recommended platform setup. |
| Maximum Take-off Weight | 42 kg |
| Maximum Payload | 8 kg |
| Maximum Speed | 30 m/s |
| Cruise Speed | 21-24 m/s |
| Stall Speed | 18 m/s |
| Endurance | 1.5-2 HoursActual endurance varies with payload, battery condition, flight profile, environmental conditions and system configuration. |
| Flight Range | 150 kmActual range varies with payload, battery condition, flight profile, environmental conditions and system configuration. |
| Wind Resistance | VTOL Level 4 / Fixed-wing Level 6Ratings distinguish VTOL from fixed-wing operation. |
| Modular Airframe | Detachable major airframe sections for transportation, assembly and maintenance |
| Landing Gear and Tail Architecture | Three-point skid landing gear and twin-boom H-tail |
| Vertical and Cruise Propulsion Architecture | Dedicated lift motors for vertical takeoff and landing; separate electric pusher propulsion for fixed-wing cruise |
| Integration Space and Purpose | Internal installation space for sensors, communications, onboard computing, power distribution and project-specific systemsInternal dimensions are reference values; actual dimensions may vary depending on platform configuration, antenna installation and integrated equipment. |
| Supplied Configuration | Complete flight platform with integrated propulsion, flight control, power distribution and actuation systemsPropulsion, flight control, power distribution and actuation are integrated as part of the confirmed platform configuration. |
| Mission Equipment Selection | Project-selected payloads, data links, communication equipment, ground control equipment and other mission-specific systemsMission-specific systems can be selected according to project requirements. |
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