APUS i-6

Fuselage
  • Length: 10.0 m
  • Width: 1.6 m
  • Height: 4.1 m
Wing
  • Area: 18.0 m²
  • Span: 15.6m
  • Aspect Ratio: 13.5
Horizontal Stabiliser
  • Gross Area: 4.0 m²
  • Span: 4.2m
Masses
  • MTOM: 2.800 kg
  • Empty weight 2.200 kg
  • Payload: 600 kg
  • 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
Performance
  • Max. Endurance: 6.0 h
  • Max. Range:  1.100 NM
  • Max. Cruise Speed:  260 KTAS
  • Min. Take-off Distance: 350 m

The APUS i-6 is a technology demonstration platform with a MTOM of 2.8t. 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 and medium-haul as well as 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 high level of modularity and interchangeability for propulsion system components. The high-voltage and high-current electrical systems will also be an area of research.
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 2 t MTOM class. This variant will be equipped with a shorter wing for use as a commuter aircraft.
Key facts:

  • Technology demonstration platform optimised for distributed electric propulsion
  • Configurable as a turbo-prop commuter
    • Choices of power source:
    • Gas turbine
    • Diesel engine
    • Fuel cell