7.2 Airframe
Carbon composite airframe
The airframe is primarily made of carbon-epoxy composite with
small amount of glass and aramid fibres, with PVC foam and
aramid honeycomb core in sandwich panels. Composite wing with
carbon main spar and an auxiliary spar carrying ailerons hinges and
flaps have a 60% of trailing edge employed as Fowler flap . Wings
and stabilizer are dismountable.
Fuselage
The self-supporting monocoque fuselage with integral fin is made
as one piece with integral interior, armrests, and floors. Interior
shell has aramid-carbon layer for better passive safety and it is
integrated into the middle part of the fuselage with added ribs. It
creates integral ergonomic cabin structure for two crew members
sitting in tandem configuration. The luggage space is located
behind the rear seat, accessible from inside, or from left side of the
fuselage. Part of central fuselage creates a 1,73m long center-wing,
used for main undercarriage retraction.
The fuselage airframe includes firewall with four engine mounting
stations, Ballistic Recovery System and front landing gear mounting
points, main landing gear and cockpit mounting points, 2+1 hinges
of horizontal stabilizer, 2 rudder mounts at the hear, together with
a bottom fin, optionally with integrated structure for a glider
towing mechanism.
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