2023 ICP Aviazone Vimana

Structure

The Vimana® is a monoplane type, with two side-by-side seats, fitted with a high wing supported by struts.

The wings are trapezoidal with aerodynamic profile NACA 23015, provided with twist & dihedral & its lift system consists of slats on the leading edge & double-slot flap on the trailing one.

The slats slide on 4 ways operated by the same amount of levers, which are handled by a torque tube.

The horizontal empennage is tapered & consist of a fixed stabilizer & a moving balancer. Both the fixed part & the moving one are carried out in two half planes. The left balancer is provided with trim wing & motor located in the front housing of the elevator with position indicator.

Cockpit

The two large lateral doors allow an easy independent access to the cabin.

The cockpit is completely sound insulated, with lining with upholstery or fitted carpet.

Excellent visibility thanks to the doors fully transparent.

The seats are in skin & side by side type.

The rudder pedals is adjustable.

Double controls are part of the Vimanas’ standard equipment.

The luggage van, situated behind the seats & accessible during the flight, may contain up to 45 lbs (20 kilograms).

It is possible to improve the cabin ventilation by using two rotating air scoops in the doors windows.

Heating system with control on the dashboard.

Cabin light.

Landing Gear

The tricycle type undercarriage is composed by a front steering wheel connected to the rudder bar & provided with shock absorber of the elastic type & by the main undercarriage composed by two Kevlar half leaf springs attached to a steel crossmember passing into the fuselage.

The braking action is exerted by disk brakes with hydraulic pliers operating on the main undercarriage wheels. The brakes are independent on the two wheels & are controlled by exerting a pressure on the pedals.

Engine / Propeller Group

The aircraft is equipped with engine Rotax 912 ULS 100 Hp with clutch & potentiated starter.

The propeller is an Ivoprop three-bladed with variable pitch in flight or a Kaspar KA1/3 LA with variable pitch in flight too (optional).

Air box with filter.

The engine cowling is completely removable to permit an easier engine van inspection.

The fuel system is provided with an additional electric pump shielded anti-heat.

The fuel system is equipped with two tanks installed into the wings & contain 36 lt. capacity each. The tanks are communicating & flow into a collection sump, placed in the fuselage, provided with drain valve & with fuel reserve indicator connected to a push-to-test light.

Sight fuel level gauge on the left wing.

Return circuit of fuel (anti vapor look)

Safety Equipment

It’s possible to install a parachute “Junkers 500” softpack type.

The flaps control has a torsion pipe that cause a linkage between the kinematism on the right half-wing & on the left one.

By causing the flaps rotation, the extraction of the slats is carried out at the same time.

Both the high-lift device & the trim are electrically actionable. Moreover there is a mechanic control manually actionable that permits the operation of the high-lift device in case of emergency.

Standard Instrumentation

Anemometer

Altimeter with setting window;

Variometer

Tachometer

Compass

Sljp & skid indicator

Fuel pressure

Oil pressure

Oil temperature

Front left head engine temperature

Rear right head engine temperature

Air box temperature indicator

Hourmeter

Voltmeter

Manifold pressure