Fusioncopter FC4 is a dualengine special category (aiming at category B according to classification regulations CS.27) gyroplane powered by two piston engines in a pushing propeller layout, designed to carry up to 4 people. It is a multipurpose
vehicle intended to operate daylight flights under VFR conditions.
The basis of success for the Fusioncopter FC4 was an extensive and advanced research and development program. Thanks to the funds of the National Research and Development Centre the program included both extensive theoretical calculations, as well as severe and thorough practical tests of all the key components of this new generation gyroplane.
A group of some of the best and most experienced engineers, scientists and experimental test pilots in the aviation industry, particularly the field of helicopters and gyroplanes, were involved in the work conducted on the FC4.
The Fusioncopter research and development was primarily focused on the safety of the craft. Very detailed research was done concerning the protection of crew’s and passengers’ life, which included the designing of the energy absorbing system for the seats, the dual propulsion system and extensive testing of the strength and durability of the construction.
In this section we present the results of these tests, according to the requirements regarding the research publication subsidized by the National Research and Development Centre. Some of them include a commentary, others are presented as raw data, open to further interpretation of the reader.
the supporting structure of the fuselage and the tail duralumin monocoque
cabin fairing honeycomb core kevlarcarbon composite
remaining fuselage fairing carbon and partly glass composite
engine hoods carbon composite tested for fire resistance
four seats in 2+2 configuration
two certified Rotax 912 S engines in pusher configuration
two dualblade constant speed type MTV21ACF/CFLD17205 MTPropellers equipped with feathering system
control system double (dualrudder)
closed cabin with left and right door, as well as an emergency drop system on both sides
type H empennage
fixed landing gear with one front wheel and two main wheels. Retractable landing gear planned in future versions.
Fourblade rotor (version a) with a 8.8 m diameter consisting of two dualblade conventional cradles facing each other at a 22,5 degree angle (this solution was tested and reported to the licensing offices in the US and EU). The rotor has a fixed pitch. It is based on aluminum blades with a 200 mm chord, using a NACA 8H12 profile.
dualblade rotor (version b) with a 11.2 m diameter in a single cradle layout, 280 mm chord aluminum blades
rotor’s prerotation drive through the left engine’s flexible shaft secured with a backstop clutch
fuselage: length without rotor: 7.268 m; width: 3.191 m; height: 3.009 m/blockquote>
Maximum weight (MTOW) 1050 kg
Minimum weight (without the rotor) 622 kg
Maximum load (crew and cargo) 300 kg
Maximum fuel weight (157l) 121,7 kg
Number of people on board 4 pax
Maximum weight of pilot/each passenger 100 kg