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Micro-Aviation Two-seat Trainer

Side-by-side two-seat single-engined high-wing monoplane with conventional three-axis control. Wing has swept back leading and trailing edges, and tapering chord; no tail. Pitch/roll control by stabilators; yaw control by tip rudders; control inputs through stick for pitch/roll and pedals for yaw. Cantilever wing; wing profile NACA 23015; double-surface. Undercarriage has three wheels in tricycle formation; suspension on all wheels. Push-right go-right nosewheel steering connected to yaw control. Brake on nosewheel. Aluminium-tube/wood/steel-tube framework, partially enclosed. Engine mounted below wing driving pusher propeller.
Seeing the need for training aircraft, Micro-Aviation decided at the end of 1981 to launch some two-seater microlights. To this end, the firm asked Don Mitchell to give it the benefit of his experience in this matter and a prototype called the Two-Seat Trainer was duly shown at Oshkosh in August 1982.
By 1983 it has not gone into serious production. The aircraft shown was a direct development of the B10 Mitchell Wing, enlarged and strengthened. It was intended that the two-seater should use a Konig SD570 four -cylinder two-stroke engine.

Engine: Konig SD570, 28 bhp at 4200 rpm.
Power per unit area 0.16hp/sq.ft, 1.7 hp/sq.m.
Wing span 38.0 ft, 11.58 m.
Mean chord 4.8 ft, 1.45 m.
Total wing area 181 sq.ft, 16.8 sq.m.
Wing aspect ratio 8.0/1.
Empty weight 240 lb, 109kg.
Max take-off weight 640 lb, 290 kg.
Payload 400 lb, 181 kg.
Max wing loading 3.55 lb/sq.ft, 17.3 kg/sq.m.
Max power loading 22.9 lb/hp, 10.4kg/hp.
Load factors +6.0, -6.0 design.
Stalling speed 24 mph, 38 kph.
Max climb rate at sea level 400ft/min, 2.0m/s.
Take-off distance 350ft, 107m.

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