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Aerostructure Pipistrelle P2



Single-seat single-engined high-wing monoplane with conventional three-axis control. Wing has swept back leading and trailing edges, and constant chord; V-tall. Pitch/yaw control by elevon; roll control by half-span ailerons; control inputs through stick for pitch/roll and yaw. Wing braced from below by struts; wing profile Worthmann FX-63-137; double-surface. Undercarriage has three wheels in tail-dragger formation; glass-fibre suspension on main wheels. Push-right go-right tailwheel steering connected to yaw control. No brakes. glass-fibre fuselage, partially enclosed. Engine mounted at wing height driving pusher propeller.

The Pipistrelle was designed by Robert Jacquet. The first second generation microlight to appear in Europe, the prototype (designated P2A) accomplished its first flights at the end of 1981 and the first sales of the production model P2B commenced in March 1982.

Built by the Aerostructure company, which specialises in aeronautical sub-contract work in civil and military aviation, this machine uses its designer's experience with composite materials and only the two struts carrying the wing are of Duralumin. The fuselage is made as two half-shells of bonded layers, while the wings and tail surfaces are fixed to the fuselage in a similar fashion to that used for gliders.

Control surfaces are operated by pushrods with sealed bearings so that the only two cables used on the Pipistrelle are those which steer the tailwheel from the rudder bar.

The production aircraft have a JPX PUL425 26 hp engine. The machine is trans-portable on a road trailer and can be rigged or derigged in 20 minutes by two people. Folded dimensions are 16.8 x 4.0 x 5.3 ft (5.00 x 1.20 x 1.60m). In France it is sold in two forms, either ready built or as a kit needing around 120 hours assembly.

Engine: JPX PUL425, 26 hp at 4600 rpm        
Propeller dia: 39 inch, 1.00 m        
Reduction: None            
Max static thrust:155 lb, 70 kg.         
Power per unit area: 0.18hp/sq.ft, 1.9 hp/sq.m.
Fuel capacity: 5.3 USG, 4.4 Imp gal, 20.0 litre.
Length overall: 16.5 ft, 5.0 m.
Height overall: 5.7ft, 1.70m.
Wing span: 36.7ft, 11.2m.
Constant chord: 3.9 ft, 1.20 m.
Dihedral: 0.5deg.
Sweepback: 1.5deg
Tailplane span: 8.2 ft, 2.50 m.
Total wing area: 146 sq.ft, 13.5 sq.m     
Total aileron area: 11.9sq.ft, 1.11sq.m.
Total elevon area: 12.9 sq.ft, 1.20 sq.m
Wing aspect ratio: 9.3/1.
Wheel track: 3.6 ft, 1.07 m.
Wheelbase: 10.6 ft, 3.20m.
Tailwheel dia overall: 8 in, 20 cm.
Main wheels dia overall: 16 in, 40 cm.
Empty weight: 54 lb, 115kg.
Max take-off weight: 446 lb, 202kg.
Payload: 192 lb, 87kg.
Max wing loading: 3.06 lb/sq.ft, 15.0kg/sq.m.
Max power loading: 17.2 lb/hp, 7.8kg/hp.
Load factors: +6, -3 ultimate.
Max level speed: 62 mph, 100 kph.
Never exceed speed: 75 mph, 120 kph.
Max cruising speed: 56 mph, 90 kph.
Economic cruising speed: 50 mph, 80 kph.
Stalling speed: 24 mph, 40 kph.
Max climb rate SL: 600 ft/min, 3.0 m/s.
Min sink rate: 200 ft/min at 34 mph, 1.0 m/s at 55 kph.
Best glide ratio: 14/1 at 34 mph, 55 kph.
Take-off distance: 100 ft, 30 m.
Land-ing distance: 82 ft, 25 m.
Service ceiling: 10,000 ft, 3050 m.
Range average cruise: 155 mile, 250 km.


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