CityHawk
Urban Aeronautics, Ltd.
Yavne, Israel
www.urbanaero.com

Urban Aeronautics Ltd. has developed advanced aerodynamic technologies that are the basis for an entirely new family of internal rotor (ducted fan) aircraft known as Fancraft™. UrbanAero capitalizes on its extensive portfolio of Intellectual Property via two subsidiary companies, Tactical Robotics Ltd. and Metro Skyways Ltd., each of which is developing unique Fancraft™ for specific markets. UrbanAero’s unmanned military Fancraft is the Cormorant and has flown extensively since 2009, including autonomous free flights since Dec. 30, 2015.

CityHawk Tech Specs
Planned technical specifications of the manned CityHawk Fancraft. (UrbanAero graphic)

Metro Skyways Ltd., a subsidiary of Urban Aeronautics plans to launch the design and development of a four-passenger, Vertical-Takeoff and Landing (VTOL), flying car based on Urban Aeronautics’ internal rotor, Fancraft™ technology. The vehicle will initially be powered by jet fuel, but will be designed from the outset to convert to liquid hydrogen and eventually also to 700 bar compressed hydrogen, once such options become commercially feasible.  Metro Skyways Ltd was established by Urban Aeronautics in 2013 to focus exclusively on developing Fancraft™ for the manned, civil market.  MSL will develop the CityHawk under a license to utilize UrbanAero’s 39 patents covering all aspects of Fancraft™ technology. CityHawk will be designed to meet FAA/EASA certification standards for manned VTOL aircraft.

CityHawk is unique in combining a compact, car-sized design that has a four passenger capacity, no exposed rotors or wings, no batteries and potential for zero carbon emissions.  Hydrogen’s only byproduct is water.  CityHawk is designed to achieve these qualities while meeting all design criteria that are the basis for eventual FAA/EASA certification.  This paves the way for true, unrestricted commercial viability.

While CityHawk will initially be piloted by a human pilot, the vehicle’s flight control and flight management systems will be capable of a high degree of autonomy from the outset.  The technology is being developed and tested on Tactical Robotics’ Cormorant prototype which already flies fully autonomously. As the technology of autonomy and regulatory infrastructure mature, CityHawk will eventually transport passengers robotically.

CityHawk’s future hydrogen power may rely on direct feed of hydrogen into a state-of-the art (FAA/EASA certified) turboshaft engine as an alternative to fuel cells, power conditioners, cables and electric motors.  This direct and compact conversion of hydrogen into shaft power, combined with UrbanAero’s unique Fancraft™ aerodynamics, makes CityHawk’s unique size and passenger capacity possible, while keeping an FAA/EASA certified primary power unit at the ‘heart of the machine’. A much larger version, the 14-seat Falcon XP (2 pilots and 12 passengers) has also been designed.

UrbanAero 's 5-seat CityHawk and 14-seat Falcon XP
UrbanAero’s 5-seat CityHawk and 14-seat Falcon XP

Falcon XP Characteristics (updated January 2018)

Basic empty weight 2,000 kg 4,400 lb
Maximum take-off weight 3,500 kg 7,700 lb
Payload plus useful fuel weight 1,500 kg 3,300 lb
Mission weight (360 kg payload Ref) 1,700 kg 3,800 lb
Maximum speed 216 kph 120 kt
Minimum fuel flow (@60 kt) 270 kg/hr 740 lb/hr
Fuel flow @ mission weight; 100 kt * 350 kg/hr 760 lb/hr
Range (Pilot +9) * 300 km + 20 min. Res. 185 mi + 20 min. Res.
Range (Pilot +13) * 180 km + 20 min. Res. 110 mi + 20 min. Res.
Estimated noise level (@ 150 feet) 80 dBA

CityHawk Characteristics (updated January 2018)

Basic empty weight 1,170 kg 2,580 lb
Maximum take-off weight 1,930 kg 4,250 lb
Payload plus useful fuel weight 760 kg 1,670 lb
Mission weight (408 kg payload Ref) 1,750 kg 3,900 lb
Maximum speed 270 kph 150 kt
Minimum fuel flow (@60 kt) 280 kg/hr 610 lb/hr
Fuel flow @ mission weight; 90 kt * 290 kg/hr 640 lb/hr
Fuel flow @ mission weight; 130 kt * 404 kg/hr 890 lb/hr
Maximum fuel 800 liter 211 US Gal
Range (Pilot +4) * 150 km + 20 min. Res. 93 mi + 20 min. Res.
Range (Pilot only) * 360 km + 20 min. Res. 224 mi + 20 min. Res.
Estimated noise level (@ 150 feet) 76 dBA

* @ Sea Level (Best Range Altitude); ISA
Note: Mission weight = Basic Empty weight + Payload + 1/2 Fuel
Specifications are subject to change without notice

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