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Aviation History
1959
1959 - 1404.PDF
FLIGHT, 15 May 1959 Helicopters of the World 683 duties: public transport with pilot, fourpassengers and luggage; pilot training with side-by-side seating and full dualcontrol; ambulance, carrying two stretchers internally and medical attendant; searchand rescue, using detachable hydraulically operated winch capable of lifting twopeople simultaneously; freight transport with jettisonable sling for external loadsof 1,000 lb; spraying and dusting for pest control and crop culture; anti-submarinedetection, using detachable pack unit con- taining sonar gear; police and coastguardpatrol, using loud-hailer unit; and water- borne operations using floats.• Rotor diam., 49ft; fuselage length, 41ft; empty weight, 4,322 lb; gross weight, 5,900 lb;economic cruising speed, 80 m.p.h.; hovering ceiling with 10ft wheel clearance in groundeffect, 6,170ft; range at economic cruising speed with standard tanks, 260 n.m. BRAZIL Centro Tecnico daAeronautica Sao Jose dos Campos. Beija-Flor From 1952 onwards, the Ger-man Prof. Henrich Focke and his team worked in Brazil on the design and pro-duction of a light helicopter within the capabilities of the Brazilian industry. TheBeija-Flor, as it is called, has now made its first flights after 40 hr of tethered tests.Power is provided by a fan-cooled Con- tinental 225 h.p. engine mounted horizont-ally in the nose, driving the rotor through a centrifugal clutch, lorry back axle adaptedfor reduction and a freewheel. The rotor has only flapping hinges at the head, dragfreedom being incorporated in articulations at mid-blade span. Cyclic-pitch variationis used only for lateral displacement. Two intermeshing, three-bladed tail rotors servefor longitudinal control by collective-pitch variation from the stick and for directionalcontrol by differential-pitch variation from the rudder pedals. The machine was de-signed to U.S. airworthiness specifications. • Rotor diam., 29ft 7in; length, 28ft llin;gross weight, 2,260 lb; disposable load (two occupants), 652 lb; max. cruising speed, 87m.p.h.; vertical climb, 197ft/min; ceiling, 12,200ft. Omnipol HC-2 Heli-Baby I CZECH OSLOVAKI A Omnipol Ltd. Washingtonova 11,Prague III. HC-2 Heli-Baby An indigenous Czecho-slovak design, the Heli-Baby is one of the lightest two-seat helicopters in the world.With a three-bladed, fully articulated rotor and dual controls, it is powered by a PragaDH flat-four piston engine giving 83 h.p. at 3,000 r.pjn. Low operating costs, sturdy construc-tion and sensitive and responsive controls are claimed to make the Heli-Baby suit-able for training as well as for a wide range of utility applications, including patrol,transport and liaison work. Practice engine-off landings can be made withoutswitching off the engine. Very low vibra- tion and noise level and excellent visibilityfrom the covered cabin are further favour- able features. The standard undercarriageconsists of main- and nosewheels and the engine is mounted behind the cabin, withits crankshaft inclined to the vertical. A metal monocoque boom carries the tail-rotor transmission, tail rotor, trimming surface and tail bumper.In one hour the Heli-Baby can carry a pilot and 220 lb of payload over 62 miles,using only 4.85 gal of fuel. The rotor blades can be rapidly dismantled for simpletransport by road or rail over long distances. The whole machine can beinspected and serviced from ground level. • Rotor diam., 28ft llin; length, 34ft 5in; empty weight, 840 lb; gross weight, 1,280 lb; hovering ceiling, with ground effect, 3,600ft; rate of climb, 710ft/min; max. speed, 78 m.p.h.; cruising speed, 62 m.p.h; range, 93 miles. FRANCE Sud-Aviation 8.N.C.A. - 37 Boulevard de Montmorency,Paris 16. SA.3200 Flight trials of this latest andlargest helicopter to come from the Sud factory at La Courneuve should now beunder way. Although designed to a joint French Air Force, Navy and Army speci-fication, civil requirements have been kept in mind and it should be capable of carry-ing 25 or more passengers. It is powered by three Turbomeca Turmo III free-shaftengines, giving 800 h.p. each, all geared to a single primary pinion which in turndrives the rotor through a reduction gear. The four blades of the tail rotor are twistedlike those of a propeller. Fully powered hydraulic control is provided, together witha SFENA 351 yaw and roll damper using rate gyros. Two hydraulic pumps and anoil cooler are driven by the transmission. All fuel is carried in streamlined tanksmounted on outriggers, the rear supports Sud SA.3200
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