What is the Minimum Order Quantity (MOQ) for custom engineering programs?

We do not enforce high volume MOQs for custom engineering programs. Customers may commission an initial A-Sample engineering batch of 1 to 4 units for bench testing and prototype flight trials before committing to volume production runs.

Can you customize the ducted fan to fit our proprietary airframe nacelle cavity?

Yes. We regularly adapt outer shroud geometries, inlet elliptical radii, and structural stator mounting lugs to match specific wing pods, fuselage fairings, or tilt-mechanism pivots without compromising internal 0.8-1.2mm tip clearances.

What bus voltages and power inverter architectures are supported?

We support DC bus voltages ranging from 100V up to 800V+. Our engineering team matches motor windings and Silicon Carbide (SiC) inverters with custom switching frequencies and dual-redundant CAN-FD communication.

Do custom units include certified test and airworthiness reports?

Every custom unit ships with a full dynamometer bench test report detailing voltage, current, RPM, static thrust, torque, acoustic emission, and thermal convergence curves. We also provide structural FEA data for aircraft airworthiness compliance.

Can you support Distributed Electric Propulsion (DEP) synchronization?

Yes. For multi-fan configurations (e.g., 6 to 12 distributed thrusters), we provide integrated electronic speed control systems with sub-millisecond bus synchronization, dynamic thrust vectoring commands, and single-engine-inoperative (OEI) redundancy.

How should an OEM evaluate payload capacity and thrust-to-weight ratio before starting customization?

OEMs should first establish the structural empty weight and battery mass fractions via the fundamental aircraft mass budget equation. For heavy-lift multirotors, net useful payload typically occupies 30% to 45% of MTOW with a required dynamic TWR of 1.8 to 2.2. For comprehensive actuator disk derivations and sizing matrices, consult our technical monograph: [Evaluating Industrial Drone Payload Capacity: Momentum Theory & Sizing Guide](/blog/how-much-weight-can-a-drone-carry-propulsion-sizing).

Home/Electric Ducted Fan/Custom Engineering & Integration

AEROSPACE POWERTRAIN ENGINEERING

Custom Electric Ducted Fan Propulsion Systems

Q: What is the standard development lead time for an A-Sample custom EDF prototype?

For bespoke nacelle aerodynamic shaping and tailored motor windings, our standard prototype turnaround is 4 to 6 weeks. This includes 3D aerodynamic CFD verification, composite tooling, motor winding, assembly, and calibrated dynamometer test data delivery.

Bespoke aerodynamic nacelles, custom high-voltage motor windings, and turnkey distributed powertrain integration for mission-critical aircraft.

Custom Aviation Electric Ducted Fan Propulsion Unit

FULL-SCALE PROTOTYPE

Thrust Sizing Scope

5kgf – 1000kgf+

Bus Architecture

100V – 800V SiC

Dynamic Tip Clearance

0.8 – 1.2 mm

Rapid A-Sample Turnaround

4 – 6 Weeks

iSystems Engineering Overview

Yuntu provides full-lifecycle custom electric ducted fan (EDF) propulsion development across 5kgf to 1000kgf+ thrust classes. Our engineering covers non-standard area ratios, aviation carbon composite layups with ballistic Kevlar containment, 400V–800V SiC motor winding optimization, and structural pylon integration. Standard prototype delivery is 4 to 6 weeks with comprehensive wind tunnel and dynamometer test certificates.

Ref:Yuntu Aerodynamics & Propulsion Integration Laboratory, Custom Powertrain Protocol 2026

Aerospace Engineering Customization Across 4 Physical Domains

When off-the-shelf commercial propulsion fails to meet constrained airframe envelopes or high-voltage bus architectures, Yuntu delivers mission-optimized bespoke propulsion engineering.

Aerodynamic Shaping

Nacelle Geometry & Convergence Area Ratio

Full Navier-Stokes computational fluid optimization of inlet lips, diffusion angles, and stator vane swirl recovery tailored to mission transition profiles.

Inlet lip radius optimization for tilt-wing transition and high-alpha inflow
Nozzle exit area ratio calibrated to cruise speed (100–280 km/h)
Ultra-tight 0.8–1.2mm dynamic tip clearance carbon shrouds

Up to +18% net static-to-cruise thrust efficiency over catalog shrouds

Structural Mechanics

Aviation Carbon Layup & Ballistic Containment

Autoclave-cured T700/T800 composite structures with integrated Kevlar containment rings complying with aerospace airworthiness standards.

Multi-axial carbon fiber plies optimized for gyroscopic bending loads
Full blade containment certified up to 120% nominal overspeed
Structural stator struts transferring up to 1000kgf thrust load into the airframe

Zero-penetration blade-out containment with minimum nacelle parasitic mass

Electromagnetic & ESC

Custom Motor Windings & SiC Inverter Tuning

Dedicated stator lamination geometries and bespoke Kv windings matched to 400V–800V Silicon Carbide aviation battery architectures.

Target Kv calibration for peak torque at specific cruise RPM sweet spot
High-voltage corona-resistant insulation (Class H, 180°C thermal endurance)
Silicon Carbide (SiC) inverters with field-oriented vector control (FOC)

96.2% motor-inverter system efficiency under continuous hover/cruise duty

Airframe Integration

Structural Pylon Mounts & Avionics Telemetry

Titanium load-bearing interfaces and redundant telemetry protocols engineered directly into the nacelle structure for turnkey integration.

Bespoke titanium/aluminum pylon bracket interfaces matching aircraft spar hardpoints
Dual-redundant CAN-FD, RS-422, and PWM bus control interfaces
Integrated temperature, vibration, and stator strain gauge telemetry channels

Turnkey mechanical and electrical drop-in readiness for flight tests

Platform Baseline Derivative Families (60kgf to 1000kgf+)

To minimize program development lead times, custom engineering programs can be derived directly from Yuntu mature baseline propulsion units.

30kgf – 90kgf

YTN-60 Derivative (Industrial Compact)

Slimline nacelle, low acoustic signature, IP67 weatherproofing

Bus: 96V – 200V DC

Target: Industrial multi-rotors, pipeline inspection VTOL, security UAVs

•Outer diameter: 320–420mm

•Weight: 4.8–6.5kg

•Acoustic emission: ≤51dB

120kgf – 300kgf

YTN-200 Derivative (Aviation Mid-Thrust)

High-voltage winding, 400V/800V SiC matching, tilt-mount pylon

Bus: 400V – 600V DC

Target: Heavy cargo multicopters, light utility eVTOL, medical express drones

•Outer diameter: 620–740mm

•Weight: 14.5–18.2kg

•Continuous power: 45kW

350kgf – 650kgf

YTN-500 Derivative (Heavy Logistics)

Kevlar ballistic containment, high-torque winding, dual-bus redundancy

Bus: 600V – 800V DC

Target: Inter-island cargo UAVs, defense heavy-lifters, unmanned fire rescue

•Outer diameter: 920–1080mm

•Weight: 38–46kg

•Full blade containment certified

750kgf – 1200kgf+

YTN-1000 Derivative (Aviation Flagship)

DEP array clustering, 800V+ SiC inverter integration, CCAR/FAA compliance

Bus: 750V – 900V DC

Target: Passenger eVTOL air taxis, regional cargo aircraft, heavy logistics drones

•Outer diameter: 1350–1520mm

•Weight: 82–96kg

•System efficiency: >96.2%

INTEGRATION CASE STUDIES

Aircraft Architecture Integration Paradigms

Engineered custom solutions developed for specific flight dynamics and airframe configurations.

eVTOL Tilt-Wing / Tilt-Rotor Pods

Vertical hover transitioning to 220 km/h forward flight

Challenge: Severe lip separation and massive pitching moments during 45° tilt transitions.

Yuntu Solution: Asymmetric cambered inlet lip with active stator swirl cancellation, maintaining attached boundary layer across 0°–90° angles of attack.

Performance Gain:+22% usable thrust reserve during transition flight phase

Heavy-Lift Multirotor Compact Array

High-precision hover in gusty conditions (Beaufort 6)

Challenge: Excessive wingspan and transport bottlenecks caused by 50-inch open propellers.

Yuntu Solution: Four-pod or six-pod ducted thruster configuration with Kevlar-reinforced composite duct walls and low rotational inertia.

Performance Gain:54% footprint reduction with 4x faster attitude step-response

Fixed-Wing Fuselage Tail-Pusher

160–260 km/h sustained economic transit

Challenge: Fuselage boundary layer turbulence ingestion and wake drag penalties.

Yuntu Solution: Boundary Layer Ingestion (BLI) conical inlet cowl with pressure-recovery stator cascade.

Performance Gain:14% reduction in cruise energy consumption per kilometer

Distributed Electric Propulsion (DEP) Wing

Continuous high-lift blown-wing operations

Challenge: Complex motor-to-motor synchronization and high drag penalty on engine out.

Yuntu Solution: Multi-thruster CAN-FD sub-millisecond dynamic thrust vectoring with automated asymmetric compensation.

Performance Gain:Sub-millisecond single-engine-inoperative (OEI) fail-safe recovery

Airworthiness Engineering Documentation Package

Every custom propulsion program delivers production-ready aerospace engineering documentation for aircraft certification.

Aerodynamic DataAIAA / ISO Aerodynamics Format

1D Momentum & 3D CFD Aerodynamic Polar Package

Calibrated thrust vs. power, mass flow, pressure distribution, and exit velocity maps across 0–300 km/h.

Mechanical CADASME Y14.5M GD&T

Native 3D STEP Envelope & Pylon Load Interface Definition

Exact mechanical envelope, mounting fastener specs, center-of-gravity (CG), and moments of inertia (MOI).

Structural FEAFAA Part 23 / CCAR-23 Guidelines

Aero-Structural FEA & Modal Resonance Analysis Report

Stress distribution under 6G maneuver loads, gyroscopic precession fatigue, and modal resonance margin.

Ballistic SafetyFAA 14 CFR § 33.19 Compliant

Blade-Out Containment Certification Dossier

Numerical simulation and physical spin-rig evidence demonstrating zero-casing penetration at 120% redline RPM.

Ground TestingISO 17025 Calibrated Rig

Official Dynamometer Bench Test Certificate

Factory-calibrated voltage, current, RPM, static thrust, torque, acoustic footprint, and thermal equilibrium curves.

Avionics ICDCAN-FD / ARINC 825 Compatible

Interface Control Document (ICD) & CAN-FD DBC Package

Complete register map, telemetry diagnostics definitions, and fail-safe throttle governance protocols.

Propulsion R&D & Test Infrastructure

Our state-of-the-art laboratory facilities ensure all performance metrics are physically measured and empirically validated.

Aero-Acoustic Continuous Wind Tunnel

60 m/s continuous airspeed, 2.5m x 2.0m test section

Inlet lip flow separation, dynamic crosswind response, acoustic array noise mapping.

1500kgf High-Voltage Dynamometer Rig

Up to 1000V DC, 1200kW electrical regenerative absorption

Step-response torque calibration, continuous endurance hovers, motor thermal saturation curves.

Aerospace Composite Autoclave Facility

2.5m diameter, 10 bar working pressure, 250°C curing

Aviation-grade T700/T800 prepreg carbon fiber consolidation with void fraction <0.5%.

Desert Sand & Environmental Chamber

50°C ambient, 0.5–50μm silica sand concentration, IP67 rain spray

Bearing seal integrity, blade leading-edge abrasion resistance, thermal equilibrium in extreme climates.

Interactive Propulsion Specification Builder

Input your airframe design parameters to calculate preliminary thrust margins and generate customized powertrain recommendations.

Aircraft Maximum Takeoff Weight (MTOW)200 kg

30kg (Light UAV)500kg (Cargo)1500kg (eVTOL)

Propulsion Configuration

DC Bus Voltage Architecture

Cruising / Transit Speed140 km/h

60 km/h (Inspection)160 km/h (Cruising)280 km/h (Fast Transit)

REAL-TIME SIZING OUTPUT

TWR: 1.9x

Estimated Total Hover Thrust Requirement

380 kgf

Target Single Pod Thrust

95 kgf / pod (4 total)

Closest Yuntu Reference Unit

60kgf - 200kgf (YTN-200 Derivative)

5-Stage Closed-Loop Aerospace Delivery Lifecycle

A formal systems engineering development process ensuring zero aerodynamic guesswork and absolute compliance with aircraft specifications.

Mission Profiling & Envelope Sizing

Aircraft MTOW, hover/transit thrust margins, voltage limits, geometric envelope

1D momentum sizing calculation sheet & preliminary space envelope CAD

Days 1 – 5

3D CFD & Aero-Structural FEA

Compressible Navier-Stokes blade optimization, modal vibration, thermal equilibrium

Complete 3D CFD aerodynamic polar report & finite-element stress cloud map

Weeks 2 – 3

Tooling Fabrication & Winding

Precision CNC negative molds, carbon autoclave curing, custom stator coil winding

Physical engineering prototype unit (A-Sample)

Weeks 3 – 5

Full-Power Rig Calibration

High-voltage dynamometer endurance, acoustic microphone array, sealing verification

Factory test calibration certificate with measured thrust-power curves

Week 6

Flight Integration & Serial Supply

Airframe flight trial telemetry tuning, production tooling lock, series manufacturing

Production tooling freeze and batch delivery schedule

Post-Trial Phase

Catalog Propulsion Units vs. Yuntu Custom Engineering

Direct quantitative comparison between standard commercial units and bespoke mission-engineered propulsion systems.

Engineering Dimension	Catalog Commercial Units	Yuntu Custom Engineered System	Mission Performance Advantage
Inlet Lip & Nacelle Aerodynamics	Fixed circular cylindrical lip	Asymmetric cambered lip tailored to forward cruise / tilt angles	+15% to +25% transition thrust reserve without flow detachment
Motor Winding & Kv Calibration	Fixed catalog winding (stepped Kv increments)	Precision winding matched to exact bus voltage & cruise RPM	Operates in peak 96%+ efficiency sweet spot under continuous duty
Airworthiness Ballistic Containment	Unshielded or heavy aluminum ring	Integrated Kevlar aramid multi-layer ballistic containment liner	FAA Part 23 airworthiness compliance with minimal parasitic weight
Airframe Structural Mounting	Generic rear faceplate bolts	Monocoque composite/titanium pylon transferring primary loads	Eliminates redundant brackets, reducing airframe dry mass by 12%
Avionics Telemetry & Redundancy	Basic PWM throttle signal	Dual-redundant CAN-FD bus with real-time temperature, vibration & current	Supports predictive health monitoring and sub-millisecond OEI fail-safe recovery

Engineering FAQ

Frequently Asked Questions on Custom Powertrain Engineering

For bespoke nacelle aerodynamic shaping and tailored motor windings, our standard prototype turnaround is 4 to 6 weeks. This includes 3D aerodynamic CFD verification, composite tooling, motor winding, assembly, and calibrated dynamometer test data delivery.

Ready to Engineer Your Bespoke Propulsion System?

Submit your airframe boundary conditions to consult directly with Yuntu aerospace propulsion engineers.