Heavy-Lift Strategic Propulsion

500 kgf (5 kN) High-Efficiency Electric Ducted Fan System

Engineered for 1.5–3.0 ton autonomous cargo eVTOL platforms, medium-altitude long-endurance (MALE) logistics aircraft, and high-speed amphibious patrol vessels. Powered by a 120 kW continuous (150 kW peak) dual-channel liquid-cooled motor housed in an aerodynamically optimized carbon composite cowl.

Fan Rotor Ø 0.60 m9 Blades / 7 StatorsTakeoff 4,000 rpmCruise 2,500 rpmIntegrated Duct, Fan, Motor & ESC
500kg Detail
500KGF
Max Static Thrust (ISA, S/L)
1.9M
Rotor Blade Diameter
1500RPM
Takeoff Rated Speed
120KW
Peak Motor Power (kW)

Reference Configuration Specifications

Standard Engineering Envelope & Baseline Performance

EDF Structure AnimationDynamic 3D Cutaway (9 Blades / 7 Stator Vanes)
Rotor Blade Diameter
1.90m
Nozzle Exit Diameter
0.72m
Duct Axial Chord
0.45m
Hub Diameter
0.24m
Max Static Thrust (ISA, S/L)
500kgf
Rotor Blade Count
12
Stator Strut Count
7
Takeoff Rated Speed
1500rpm
Cruise Rated Speed
2500rpm
Peak Motor Power (kW)
120kw
System ComponentsDuct, fan rotor, electric motor, and matched ESC.
Voltage & ControlTailored to customer requirements (100V–400V+ DC, CAN/PWM).
Cooling RequirementEvaluated based on airframe installation & mission duty cycle.

Propulsion Engineering Innovations

Combines ultra-high electrical efficiency with fault-tolerant dual-winding safety and severe sandstorm/coastal environment durability.

Dual Three-Phase PMSM

120 kW Redundant Dual-Winding Motor

Features electrically isolated dual-channel stator windings. In the event of an inverter or phase leg fault, the propulsion unit maintains over 60% rated thrust, ensuring critical climb gradient safety.

120 kW
Continuous Shaft Power
High-Bypass Nacelle

Diffusion Duct Aerodynamic Optimization

1.9m wide-aperture composite cowl with boundary layer ingestion (BLI) diffusion geometry. Achieves an 18% reduction in specific energy consumption during forward cruise compared to traditional open rotors.

1.9 m
Shroud Outer Diameter
Sand & Salt Barrier

Inertial Sand-Separation & Hardened Leading Edges

Nickel-cobalt electroplated rotor blade leading edges and integrated labyrinth sand-shedding nacelle contours, rigorously proven in 100-hour desert sandstorm test chambers.

IP67
Environmental Ingress Rating
High-Efficiency SiC Drive

600V–800V Wide-Bandgap Motor Controller

Silicon Carbide (SiC) MOSFET architecture delivering 98.5% peak electrical conversion efficiency with advanced partial-discharge suppression at altitudes up to 5,000m MSL.

98.5%
Inverter Peak Efficiency

Target Aircraft Configurations

Directly validated power distribution models for heavy regional freight drones and 2–4 place utility electric aircraft.

Heavy Autonomous Cargo Drone

1.5–2.8 Ton Heavy Freight Logistics Aircraft

Quad-thruster or hex-thruster tilt-wing configuration providing 20–30 kN total hover thrust with 500+ kg payload capacity across 350 km logistics corridors.

Propulsion Layout:4–6 Distributed Thrusters
Thrust Target:T/W = 1.25 – 1.30
Target MTOW:1,800 – 2,800 kg MTOW
Light Utility Commuter

2–4 Place Electric Personal & Training Aircraft

Fuselage-integrated or wing-pylon mounted twin pusher configuration offering whisper-quiet takeoff profiles and reduced runway climb distances.

Propulsion Layout:Twin Pusher / Blown-Wing Nacelles
Thrust Target:Cruise T/W = 0.30 – 0.38
Target MTOW:1,200 – 1,800 kg MTOW
Fast Coastal Patrol Vessel

High-Speed Hydrofoil & Amphibious Support Craft

Surface-skimming aeropropulsion avoiding underwater debris damage and cavitation erosion while delivering rapid acceleration up to 55 knots.

Propulsion Layout:Dual Aft Pylon Nacelles
Thrust Target:High-Thrust Static Acceleration
Target MTOW:3,000 – 6,000 kg Hull

Aerospace Engineering Deliverables

Comprehensive digital integration assets provided directly to airframe structural and avionics development teams.

Static, Transition & Cruise Aerodynamics

Full-Scale Wind Tunnel 6-DoF Calibration Dataset

High-precision load cell datasets covering airspeeds up to 55 m/s and continuous yaw/pitch deviations, enabling precise flight control simulator modeling.

Format:CSV, MATLAB & PDF Reports
Mechanical, Center of Gravity & FEA Boundaries

Parametric 3D CAD & Digital Twin Package

Millimeter-accurate mounting interface coordinates, detailed mass property matrices, and structural finite element models (Nastran/Ansys).

Format:STEP / IGES / Parasolid
Redundant Telemetry & CAN/ARINC Bus Specification

Flight-Control Avionics Interface (ICD)

Complete bus communications manual supporting CAN Aerospace, ARINC 429, and PWM fallback lines with hardware watchdog monitoring.

Format:ICD & Communication Protocols
High-Altitude Density & Thermal Envelope Matrix

Multi-Altitude Propulsion Performance Map

Comprehensive thrust, torque, RPM, and cooling fluid temperature charts mapped across 0 to 5000m ISA density altitudes.

Format:Lookup Tables & Interpolation Code

Need Full 3D CAD/STEP Models & Avionics Protocols?

Yuntu provides OEM aircraft design teams with mounting flange CAD, mass moment matrices, and CAN/ARINC ICDs.

Frequently Asked Questions

At density altitudes between 2,000m and 4,000m, air density drops by 18% to 33%. Our motor controller incorporates an active altitude-compensation curve that safely increases rotor RPM within thermal boundaries, mitigating static thrust decay to under 12% at 3,000m MSL.

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