TYPE: Tandem-seat sportplane kitbuilt.
PROGRAMME: Concept phase began June 1997; design started 1998; officially launched April 1999 after trials with two radio-controlled scale models; engineering phase, dynamic (radio-controlled) model flight tests and wind tunnel test activity completed October 1999. Full-scale engineering mockup shown at EAA AirVenture, Oshkosh, July 2000; detail design started two months later; prototype construction began mid-2001; debut planned for EAA AirVenture at Oshkosh, July 2001, but failed to occur. Rolled out 21 April 2002 and first flight eventually made (HB-YKS) on 29 May 2002. Original name of Aeris was changed to Aeriks in July 2002 due to pre-existing trade name protection in US. Public debut at EAS rally, Lodrino, 16-18 August 2002. Production of kits began October 2002. Prototype had flown 29 hours by early May 2003; Swiss Experimental category type approval then expected by end of that month, with deliveries planned to start in June 2003; however, neither had been reported by mid-December 2003.
CUSTOMERS: Orders reported from customers in France, Germany, Italy and Switzerland.
COSTS: US$69,500 (2003).
DESIGN FEATURES: Three lifting surfaces aerodynamic configuration; single pusher engine. Straight-tapered, low-swept (4° at 25 per cent chord) main wing amidships, with 2° dihedral from roots, features natural laminar flow sections based on NASA NLF(1)-0215F; main wing twist (2° 30' washout from root chord) and planform are selected for stable low-speed characteristics. Foreplane aerofoil Wortmann FX-75-141 (4° sweepback at quarter-chord), 6° anhedral. Lifting surfaces relative setting angles optimised for low drag at normal cruising speed. Standard symmetrical sections on T-tail configured, 30° swept horizontal surface. Separate fins above and below fuselage (lower portions serve as over-rotation bumper and propeller strike protector); rudder in upper vertical fin.
Quoted build time 1,000 to 1,500 hours, plus 200 to 400 hours for fully retractable landing gear option.
FLYING CONTROLS: Mechanical via push/pull rods for both ailerons and T-tail-mounted elevators; in steel cables for rudder control. Foreplane flaps have electric trim. Electrically actuated single-slotted flaps on main wing, synchronised with plain flaps on foreplanes; all flaps can be partially deflected for T-O; landing flap setting is 40° on main wing, 20° on foreplane (relative to wing chord).
STRUCTURE: All-composites. Main wings detachable for storage and/or transportation; C-section carbon fibre main spars and rear auxiliary spars; 30 per cent chord single-slotted flap and 25 per cent chord aileron in each wing; galss fibre ribs. Monocoque fuselage. Primary structures built from wet laminated glass fabric or prepreg carbon fabric, laid-up on CNC milled female moulds; all shells of honeycomb core sandwich. Glass fibre flaps and control surfaces with carbon fibre reinforcement. Primary foreplanes and tail assembly of carbon fibre C-spars, composites ribs and glass fibre-based honeycomb core sandwich skins.
LANDING GEAR: Tricycle type. Electrically actuated nose gear retracts rearward into fuselage; non-retractable main gear units on cantilever self-sprung glass fibre struts with Cleveland heavy-duty disc brakes and wheels. Nosewheel steerable by differential braking. Hydraulic mainwheel brakes and parking brake.
POWER PLANT: One Diamond Engines GIAE-110R rotary engine (78.3 kW; 105 hp), driving a three-blade constant-speed MT-Propeller MTV-7-D/RD157-106 pusher propeller via an aluminium driveshaft. Maximum propeller speed 2,500 rpm. Engine is mounted far aft of passenger cabin and has two NACA-type scoop air inlets under main wingroot and ventral airscoop for main radiator cooling. Electrically actuated cowl flap integral with port-side NACA inlet. Fuel in single 110 litre (29.1 US gallon; 24.2 Imp gallon) integral fuselage tank aft of passenger seat.
ACCOMMODATION: Pilot and co-pilot or passenger in tandem in individual cockpits; dual sidestick controls. Separate one-piece flush-type canopies, hinged on starboard side. Baggage compartment, capacity 20 kg (44 lb), under passenger seat. Central carbon fibre roll bar for flip-over protection.
SYSTEMS: Single voltage (14 V DC) electrical system powered by two engine-driven generators to provide power for gear and flap extension/retraction; main buspowers flaps, trim, landing gear, main fuel pump and other flight-essential equipment.
AVIONICS: To customer's requirement. Can be equipped to full IFR standard.
EQUIPMENT: Anti-collision stroble light and navigation light in each wingtip; one white strobe light in tail tip.