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Aviation History
1961
1961 - 0628.PDF
638 FLIGHT,II May 1961 Cessna Skyhook Del Mar DH-IA VTOL INTERNATIONAL SURVEY elements specialized fuselages may beattached, making it possible for one basic aircraft to be used for a wide variety ofapplications. One such application is seen in the recently completed primary groundtrainer, embodying the basic helicopter and a special ground effect platform. When theengine is on an air cushion is produced allowing the platform to move freely in anydirection. The helicopter is attached through a simple ball joint and scissorsmechanism which enables it to rotate in azimuth, move up or down vertically, andtilt in any desired direction. Doak Aircraft Co Inc Torrance, California Model 16 Comparatively little informa- tion is available on this VTOL/STOL research aircraft, the military designation of which is VZ-4DA. The engine is a Lycom- ing YT53 of 840 s.h.p. and provision is made for a pilot and an observer. Ducted fans at the wing-tips can be rotated through 90° and can function as helicopter rotors for vertical take-off and landing and hovering. At a safe height after take-off the ducts are rotated to a forward-facing attitude making possible much higher cruising speeds than achieved by conventional helicopters (a maximum of 230 m.p.h. is reported). The engine is fitted with a long tailpipe and hori- zontal and vertical vanes are hinged at the jet efflux to assist control during low speed and vertical flight. The ducted fans and portions of the fuselage are fabricated from Fiberglas. • Span, 25ft 6in; length. 31ft. Gyrodyne YRON-I Doak Model 16 Doman Helicopters Inc Danbury, Connecticut D-10 Powered with a Lycoming ISO-720engine of 400 h.p., this is a development of the Doman LZ-5-2 described in previousissues. In the absence of new information from the makers we quote a report of amember of Flight's staff who flew in the earlier machine: "Perhaps the most attrac-tive feature is the totally enclosed self- lubricating rotor hub. mounting the fourhingeless blades; control is effected by tilting the gimbal-mounted rotor-head. Thesix passengers occupy seats angled out towards the sizeable windows, and withseats removed the concertina doors on each side fold to give a completely unrestrictedaccess for large items of cargo. The eight- cvlinder Lycoming engine is inclined low inthe nose, and drives via a shaft passing between the pilots up to the rotor-head. Inthe air the LZ-5 demonstrated great tractability, with sufficient reserve from anengine of only 400 h.p." The D-10 is being built in Palermo,Sicily, under the designation Doman Ambrosini D-10A. The suffix "A" denotesthat the engine is the Lycoming IO-720 instead of the supercharged ISO-720. Thefollowing data apply to the D-10 model. • Rotor diam, 48ft; length, 58ft 6in; height,10ft 6in; empty weight. 3,3271b; gross weight. 5,5001b; max speed. 104 m.p.h. Fairchild Engine & Airolane Corporation Hagersto wn. Maryland M-224-1 Known to the US Army as theVZ-5FA, this experimental VTOL aircraft employs the deflected slipstream techniciueto a remarkable extent. The action of the special flaps can be seen in the picture. AGeneral Electric YT58 shaft turbine of 1,204 h.p. drives the four propellers. Grossweight for VTOL testing is about 4,0001b. Gyrodyne Company of America Inc St. James. Long Island, N. Y.YRON-1 Rotorcvcle The Rotorcvcle is being evaluated by the US Marines for themany tactical uses of which it is capable, e.g., liaison, reconnaissance, photography,mine detection, wire-laying and re-supply. It incorporates a co-axial rotor systemclaimed to give it outstanding flying qualities in all regimes of flight and toreduce pilot-training time by virtue of the relative simplicity of the pilot's task. Theengine is a Porsche GP-702 delivering 72 h.p. Under US Navy contract the Rotor-cycle has been equipped with automatic stabilization and remote control equipmentto permit operation as a drone, controlled from a ground station. Discussions havebeen opened with the FAA regarding certi- fication for commercial use. • Rotor diam, 17ft; fuselage length, lift:emptv weight. 5501b: gross weight, 8321b; cruising soeed, 59 m.n.h.: max sneed. 78m.n.h.; max endurance 0.93hr; vertical rate of climb. 910ft/min; hovering ceiling in groundeffect. 7.300ft: service ceiling. 12.400ft: max range. 48 n.m. Hiller Aircraft Corporation Palo Alto, California 12E The Model I2E for 1961, which hasan earlier militarv counterpart in the H-23D Raven, is described as the most powerfulhelicopter in the light utility class. Dual carburetters are standard and in conjunc-tion with high-compression pistons raise the power of the Lycoming VO-540 engine to Doman LZ-5 Fairchild VZ-5FA Hiller I2E 340 h.p. Accessories include floats; twincargo racks with quick-release fittings; quick-release cargo hook; complete hy-draulic rescue hoist; spraying gear; dual controls; night lighting equipment (includ-ing two revolving beacons); cabin heater and defroster; main rotor brake; specialcabin interiors and soundproofing. • Rotor diam, 35ft 5in; length, 40ft 6in:cruising speed, 90 m.p.h.; hovering ceiling in ground effect. 10,000ft; rate of climb at s.l..1.340ft/min; service ceiling, 15,600ft; endu- rance. 3.2hr. E4 This is a four-seater which can be obtained either brand-new or as a kit conversion of the three-seater 12E. Sound- proofed interiors are available for executive versions. YROE-1 Rotorcycle The Hiller companystate that the type represents the minimum practical size in helicopters. It achieves agross-to-empty weight ratio of about tv J— claimed to be a value unprecedented inmechanically driven helicopters. The en.'ine is now a Porsche of 62 h.p., develi nedspecifically for the aircraft. Primarih YROE-1 is being developed for milapplications, although a civil version prospect. A licence is held by Helicorof Paris, and a batch has been constri by Westland's Saundcrs-Roe division. The characteristics of this tilt-' the try in \tr ,-d X-18 research aircraft are seen in the photogr
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