English name: Impulse

TYPE: Two-seat lightplane.

PROGRAMME: Preliminary design started early 1994. Registration PH-VXM reserved March 1997. Main fuselage moulds completed early 1999. Main wings due to be completed by mid-2001, but this slipped to 2003 due to redesign work. The landing gear was due for completion by mid-2003. Certification to JAR 23 being undertaken under supervision of Prof dr ir Theo van Holten (flight performance); Prof dr ir J A Mulder (stability/control), ir F van Dalen (construction); Prof ir R J Zwaan (aero-elasticity); ing K van Woerkom (systems); ir van Badegom (fuel and propulsion systems).

DESIGN FEATURES: Twin-boom layout with pod-type fuselage and high wing of parallel chord; swept fins.

FLYING CONTROLS: Conventional and manual. Actuation by pushrods (ailerons and elevator), with cable and pushrod interconnected twin rudder and nosewheel system. Servo-actuated electric pitch trim and electrically operated single-slotted flaps.

STRUCTURE: All-composites wing with GFRP sandwich skin and spars; GFRP tail unit. Some GFRP parts will be produced by resin transfer moulding process. Fuselage steel tube frame with glass fibre shell will be used to finalise design of cockpit and control systems.
Wing section NACA 633415 with RA163CW3 flaps; twin tailbooms joined by NACA 0012 section horizontal stabiliser.

LANDING GEAR: Non-retractable tricycle type; GFRP cantilever sprung mainwheels. Non-steerable nosewheel; mainwheels have 45 cm (17¾ in) tyres pressurised to 3.14 bar (45.5 lb/sq in). Hydraulically operated brakes on mainwheels.

POWER PLANT: One 74.6 kW (100 hp) Mid-West AE110R rotary engine driving a three-blade fixed-pitch propeller. Fuel capacity 65 litres (17.2 US gallons; 14.3 Imp gallons) in single tank located between cockpit and engine. Oil capacity 3.0 litres (0.8 US gallon; 0.7 Imp gallon).

ACCOMMODATION: Side-by-side seating for pilot and passenger under one-piece, Perspex canopy. Baggage space behind seats.


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