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Pipistrel Apis-Bee


Apis/Bee is a single-seat middle wing ultralight self launching glider with a T- tail. All plastic parts are made in AFK, GFK and CFK technology while all main parts are LN certified. The plane itself is made of armoured plastic in combination of epoxy resin enforced with honeycomb, glass, carbon and kevlar fibers, featuring the same wing and tail section aerodynamics as the Sinus and Taurus. The wings are made in sandwich construction. Top and lower surfaces are made first then all additional elements (main spare, basic ribs, air-brake enclosure) are glued into top half. Air-brakes expand from the top half of the wing only. The rudder is built the same way from two halves with built-in control connections and hinges.

The fuselage is built in combined AFK and CFK manner as a combination of shell and sandwich construction. The two halves are are built so that most of the elements are glued into one of them and then both are put together. Carbon and kevlar are used from nose to wing section, while the rest is made in sandwich construction. The cockpit is covered with a single piece Plexyglass cover opening forward. Pitot tube and air vent (for ventilating the cockpit) are built into the nose. Static pressure is measured on the side of the fuselage. A radio antenna is built in to the aft vertical stabilizer. The tow tie is mounted on the lower front part of the fuselage. Rudder pedals are adjustable.

Horizontal stabilizer and rudder are made the same way as wings: in sandwich construction. All controls hook up automaticaly. Air-brakes and ailerons use rigid connections (tubes and bearings). Landing gear is a non-retractable wheel with disk brake under the cockpit and a small one on the tail. The wheel brake is accessible by air-brake handle.  

The basic price includes the 14.97 m wing-span tail-wheel single seater ul class glider with integrated winglets, t - tail ready to fly, test flown. Standerd are a 4 point seat belts, a defogging system for the canopy, 6 stage positive and negative deflecting flaperons, self locking Schempp-Hirth type airbrakes, spring-type elevator trim, in flight adjustable rudder pedals, 4? main wheel with disc brake and fairing, two wingtip wheels, 2 ½ in x 1 in, with fairings, steerable tail wheel 180 x 45 mm (7 in x 1 ¾ in), 14 - liter fuel tank, Hirth F33bs or Rotax 447 belt drive engine, high capacity dry-type battery 12 v / 10ah, modular electric system with fuses on primary and secondary circuit, electric starter, regulator-rectifier, fully automatic engine control and propeller positioning system, 2 blade wooden propeller reinforced with fiberglass, and an instrument panel with:
master switch key, switches with fuses and warning lights, magnetos switches,
instruments: multifunction instrument to control the engine operatiom and the system
to retract the engine, engine hours counter, rpm counter, cht, egt, altimeter,
airspeed indicator, variometer, libelle (slip indicator) & magnetic compass with mount.

Wing span: 14.97 m
Wing area: 12.24 sq.m
Aspect ratio: 18.33
Fuselage length: 6.26 m
Overall height: 1.3 m
Empty weight: 215 kg
Single wing weight: 40 kg
Max. takeoff weight: 322.5 kg
Min. takeoff weight: 250 kg
Max. speed Vne: 220 km/h
Max. airspeed in rough air: 144 km/h
Max. airspeed in aero-tow: 144 km/h
Manouvering airspeed: 144 km/h
Max. speed with air-brakes: 220 km/h
Min. speed MTOW: 60 km//h
Airfoil type and ratio: IMD 029 17.01 %
Best glide ratio @ 94 km/h: 39-1
Min. sinking rate @ 84 km/h: 0.59 m/s
G load limits: +5.3 -2.65



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