A cargo drone needs propulsion matched to its payload, route and operating conditions. Review the mass budget and available thrust before choosing a unit count or thrust class. Yuntu supplies 60–1000 kgf electric ducted fan propulsion units and integration support for aircraft developers and institutional operators.
This page covers propulsion supply and integration for cargo aircraft projects. Complete aircraft sales are outside the offering described here.
A cargo drone is an uncrewed aircraft designed to transport goods. It may use rotors, a fixed wing, or vertical takeoff combined with wing-borne cruise. Its useful load and route length depend on the aircraft's mass, energy budget and installed propulsion, together with the conditions of the mission.
Start with the delivery task: the heaviest load, the route with that load, the landing sites and the operating conditions. These inputs help separate aircraft requirements from propulsion-unit ratings.
In the United States, Part 107 applies to drones weighing less than 55 lb at takeoff. FAA guidance describes a Section 44807 exemption application route for operations outside the weight limit.[1] The FAA also sets out a Part 135 certification process for package-delivery operators.[2]
Compare landing access, hover requirements and route length before choosing an aircraft layout.
If the project uses a hybrid-electric energy system, review the engine, generator and battery duties alongside the propulsion layout. Explore hybrid drone powertrains.
A cargo drone's payload, energy and thrust reserve share the same aircraft budget. Review them together at the intended takeoff mass.
m_takeoff = m_empty + m_energy + m_payload
m_payload = m_allowable − m_empty − m_energy
m_allowable = min(m_structural_limit, T_available / R_target)
All mass terms are in kg; thrust in this expression is in kgf. Reserve energy belongs inside the battery or fuel budget and is not subtracted again as a separate mass. The thrust-based limit is a sizing estimate; structural limits and the intended operating conditions still apply.
At a fixed takeoff mass, more payload can leave less mass available for batteries or fuel. A change in aircraft weight can also change power demand. Evaluate hover, climb, cruise, delivery and reserve together, and compare range at the payload actually required.
Include sling motion, winch operation and changes in weight or balance during delivery in the mission review. These conditions require aircraft-level assessment alongside thrust sizing. Explore sling-load stability for heavy-lift drones.
For a cargo drone, compare total available thrust with the loaded takeoff mass, then repeat the calculation after removing one equal-rated unit. The examples below show arithmetic only. They do not establish an aircraft's controllability, operating limits or landing capability after a failure.
| Configuration | Total thrust | Takeoff mass | T/W, all units | Thrust, one unit out | T/W, one unit out |
|---|---|---|---|---|---|
| 6 × 200 kgf | 1,200 kgf | 600 kg | 2.00 | 1,000 kgf | 1.67 |
| 6 × 200 kgf | 1,200 kgf | 800 kg | 1.50 | 1,000 kgf | 1.25 |
| 6 × 200 kgf | 1,200 kgf | 1,000 kg | 1.20 | 1,000 kgf | 1.00 |
| 8 × 500 kgf | 4,000 kgf | 2,000 kg | 2.00 | 3,500 kgf | 1.75 |
| 8 × 500 kgf | 4,000 kgf | 2,700 kg | 1.48 | 3,500 kgf | 1.30 |
| 8 × 500 kgf | 4,000 kgf | 3,200 kg | 1.25 | 3,500 kgf | 1.09 |
A T/W of 1.00 means thrust equals weight in this simplified comparison. It says nothing about the distribution of forces, attitude control, gust response or transient performance. Define the required margin through the aircraft's engineering and validation process.
Yuntu supplies four standard thrust classes. A unit's thrust rating is not an aircraft payload rating; select the class together with unit count, installation and mission conditions.
| Thrust class | Product details |
|---|---|
| 60 kgf | View product |
| 200 kgf | View product |
| 500 kgf | View product |
| 1000 kgf | View product |
Compare the installed systems against the same cargo mission. The checklist focuses on people, lines, landing sites and the aircraft's mass and energy budgets.
| Factor | Ducted fan: check | Open rotor: check |
|---|---|---|
| Loading and unloading | Keep personnel clear of the inlet and outlet; standard procedures still apply. | Define personnel clearance around the exposed rotor disk; standard procedures still apply. |
| Sling lines and winch cables | Keep lines clear of the inlet, outlet and rotating components. | Keep lines clear of exposed rotor disks. |
| Pads and decks | Include outer duct size, mounting and installation clearance. | Include rotor swept area and operating clearance. |
| Dust, spray and loose cargo | Assess outlet flow at the actual loading and landing sites. | Assess rotor wake at the actual loading and landing sites. |
| Hover power | Compare installed power at the required thrust and operating conditions. | Compare installed power at the same required thrust and conditions. |
| Cruise | Include duct installation drag and the duty of lift units during cruise. | Include rotor installation drag and the duty of lift units during cruise. |
| Mass budget | Include the duct, mounts and related installation hardware. | Include rotor mounts and any required protective structures. |
| Selection basis | Review enclosure and site constraints alongside energy and mass. | Review rotor area and site constraints alongside energy and mass. |
Neither option wins every mission. Compare payload, route, installation and operating procedures before choosing. See the general VTOL comparison, the ducted fan vs propeller analysis and the disk loading guide.
Use the mission to define the inputs for a cargo drone propulsion review. The examples below do not assign a payload capacity or thrust class to a route.
Move goods between vessels, ports and offshore facilities.
Transport goods between mainland and island sites.
Deliver materials to sites with limited road access.
Plan deliveries to disrupted or difficult-to-reach locations.
Move parts and consumables around industrial facilities.
Transport time-sensitive supplies to clinics and communities.
A cargo drone is an uncrewed aircraft designed to transport goods. It may use rotors, a fixed wing, or vertical takeoff combined with wing-borne cruise. Its useful load and route length depend on the aircraft's mass, energy budget and installed propulsion, together with the conditions of the mission.
Start with the allowable takeoff mass and subtract empty aircraft and equipment mass, then battery or fuel mass. Include reserve energy in the energy budget without subtracting it twice. Available thrust also constrains the sizing estimate. A propulsion unit's kgf rating is not the aircraft's payload capacity; check the complete aircraft at the intended mission conditions.
Range depends on usable energy, payload, aircraft layout and the power required through the mission. Include hover, climb, cruise, delivery and reserve rather than comparing a single flight segment. Review the route with the required payload and the return condition. For hybrid projects, include the engine, generator and battery duties in the same assessment.
Begin with landing access, hover requirements and route length. Compare multirotor, winged VTOL and fixed-wing layouts against those inputs, then include installation mass, transition requirements and mission energy. Select the propulsion with the aircraft developer so that a thrust rating is assessed in the context of the complete layout.
Compare the installed systems for the same payload, route and sites. Include personnel clearance, sling lines, inlet and outlet flow, installation mass, hover power and cruise drag. A surrounding duct changes the installation, but does not replace operating procedures. Neither option wins every mission; choose using the aircraft's requirements and validation results.
The project must define its required thrust margin at the loaded takeoff mass. Calculate thrust-to-weight ratio using available thrust, then repeat the arithmetic for the selected failure condition. There is no recommended ratio on this page. The target depends on the aircraft, operating conditions and engineering validation, not the payload figure alone.
With N identical units, removing one leaves (N−1)/N of their summed thrust ratings: 75% for four units, 83.33% for six and 87.50% for eight. This is arithmetic, not a demonstrated failure capability. Thrust distribution, control response and installation conditions must also be evaluated before making any claim about continued flight or landing.
This page does not price complete aircraft. The offering is electric ducted fan propulsion supply and integration support. To request a propulsion quotation, share the aircraft layout, payload, route, target takeoff mass and planned unit count. Our team can then review the configuration and discuss the scope of supply and integration.
Requirements depend on the aircraft and operation. FAA guidance explains Part 107's weight limit and a Section 44807 exemption route.[1] It also describes Part 135 certification for package-delivery operators.[2] EASA lists international IFR flights of certified cargo drones among examples discussed for its certified category.[3] These references do not establish approval for a particular project.
Yuntu supplies electric ducted fan propulsion units in the 60, 200, 500 and 1000 kgf classes, together with sizing and integration support. This page is intended for aircraft developers and institutional operators reviewing a propulsion system. Complete aircraft sales are outside the offering described here; share the mission inputs to discuss the propulsion scope.
Discuss payload, routes and propulsion integration requirements with our team.
Supply of propulsion units is subject to applicable export control regulations and end-use review.
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