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APUS i-6

  • Area: 18m²
  • Span: 15.6m
  • Aspect Ratio: 13.5
  • Length: 10m
  • Height: 4.1m
  • Width: 1.6m
Horizontal Stabiliser
  • Gross Area: 4m²
  • Span: 4.2m
  • MTOM: 2,800kg
  • Empty Weight: 2,200kg
  • Payload: 600kg
  • Crew: 1
  • Pax: 5
Propulsion (max. cont. pwr / max. pwr)
  • Diesel Gen-set (electrical power) : 500/700 kW
  • RR M250-B17 (shaft power): 450/450 kW
  • Fuel-Cell (electrical power): 230/400 kW
  • Electric power units / nacelles (qty.): 7
  • Max. Endurance: 6h
  • Max. Range: 1,100 NM
  • Max. Cruise Speed: 260 KTAS
  • Min. Take-off Distance: 350m

The APUS i-6 is a technology demonstration platform with 2.8t MTOM. The aircraft has been developed as part of the IBEFA*alliance and will be used for testing and certifying various types of hybrid propulsion system for use in small medium-haul and eVTOL aircraft. In all regards the APUS i-6 has been configured for optimum integration of distributed propulsion systems. Up to seven electric power unit nacelles can be installed. Compatible power sources include gas turbines, diesel engines and fuel cells. The large CG range granted by the canard permits an extremely high level of modularity and interchangeability for propulsion system components. The high-voltage and high-current electrical systems will be researched with a scientific approach. Furthermore, certification aspects, such as reliability, lightning protection and electro-magnetic compatibility, are to be investigated.

Alternatively, the aircraft can be equipped with a conventional turbo-prop engine and used in the 2t MTOM class. This variant will comprise a shorter wing for use as a commuter aircraft.

Key facts:

  • Technology demonstration platform optimised for distributed propulsion
  • Also designed for turbo-prop configuration
  • Choices of power source
    • Gas turbine
    • Diesel engine
    • Fuel cell