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The Falcon-10 is a fixed-wing unmanned aerial vehicle designed for extended-range missions. Built around a tailless delta-wing airframe with blended wing-body integration, the platform combines a compact wingspan with a large effective lifting area. The airframe supports a maximum take-off weight of 180 kg and accommodates payloads up to 50 kg through an open modular payload bay. With a maximum flight range of 2,000 km and endurance of 12 hours, the Falcon-10 is suited for long-duration operations including aerial surveying, infrastructure inspection, environmental monitoring, and logistics support. The system supports both pneumatic catapult launch and rocket-assisted launch, enabling deployment without a prepared runway.
The Falcon-10 employs a tailless delta-wing layout combined with a blended wing-body design. This configuration provides a larger effective lifting area relative to its 2,590 mm wingspan, contributing to aerodynamic efficiency and flight stability. The simplified structural design reduces component count, supporting manufacturing consistency and field maintenance.
The platform supports two launch methods: high-pressure pneumatic catapult launch and rocket-assisted launch. Pneumatic catapult launch is suited for repeated deployment operations, while rocket-assisted launch enables takeoff in complex terrain or high-payload configurations. Neither method requires a conventional runway.
The Falcon-10 is powered by a 550 cc gasoline engine rated at 53 HP (39 kW). The fuel tank holds 110 L of gasoline, supporting the stated 2,000 km range and 12-hour endurance. The propulsion system provides sufficient power reserve for climb performance and cruise efficiency.
The aircraft uses a modular avionics architecture, allowing installation, replacement, and upgrading of electronic systems. The open payload bay accommodates mission-specific equipment, and the optimized internal wiring layout supports system reliability and maintenance access.
Item | Parameter |
Wingspan | 2590 mm |
Aircraft length | 2620 mm |
Max Payload | 50 kg |
Max Take-Off Weight | 180 kg |
Operation Temperature | -25°C-60°C |
Min Turning Radius | 400 m |
Rate of Climb | |
Rate of Climb | 4-5 m/s |
Cruising Speed | 180 km/h |
Max Speed | 230 km/h |
Wind Resistance | Level 7 |
Max Flight Range | 2000 km |
Max Endurance | 12 h |
Max Flight Altitude | 3000 m |
Fuel Type | Gasoline |
Fuel Tank Capacity | 110 L |
Engine Power | 550CC, 53HP / 39Kw |
Take-off Method | Air-pump catapult launch |
The Falcon-10's range and payload capacity make it applicable to several commercial and industrial use cases. These include large-area aerial mapping and photogrammetry, power line and pipeline inspection, forest fire monitoring, maritime patrol, and cargo delivery in remote regions. The dual-launch capability supports deployment from sites without runway infrastructure, such as mountainous terrain or coastal locations.
The Falcon-10 is manufactured in an ISO-certified facility. The manufacturer offers OEM and ODM customization, including payload integration and airframe modifications for enterprise customers. Technical support, spare parts supply, and operator training are available to commercial users.
The Falcon-10 has a maximum flight range of 2,000 km and a maximum endurance of 12 hours, based on the manufacturer's specifications under standard cruise conditions.
The Falcon-10 supports high-pressure pneumatic catapult launch and rocket-assisted launch. Neither method requires a conventional runway, allowing deployment from varied terrain.
The maximum payload is 50 kg, within a maximum take-off weight of 180 kg. The modular payload bay supports integration of mission-specific equipment.
The Falcon-10 uses gasoline. The fuel tank capacity is 110 L, and the engine is a 550 cc unit rated at 53 HP (39 kW).
