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Aviation History
1963
1963 - 1311.PDF
FLIGHT International, 25 July 1963 137 Brantly Helicopter Corporation Municipal Airport, Frederick, Oklahoma B-2A This version of the little Brantly two-seat helicopter, introduced during the past year, has a redesigned cockpit "glass house" which has almost dispensed with the familiar blisters over the heads of the occupants. It retains the unique Brantly three-blade main rotor, which is made of aluminium, with a polyurethane core, and has articulated inboard flapping hinges near the hub, and coincident flap and lag hinges offset 51.85in from the hub. The power plant is a 180 h.p. Lycoming VO-360, mounted vertically with induction cooling. In December 1962, British Executive Air Services acquired licence rights to manu facture the B-2A in Britain. Initially, this company will assemble B-2As manufactured by the parent company. Rotor diam, 23ft 9in; length of fuselage, 21ft 9in; height, 6ft Him; gross weight, 1,6001b; empty weight, 1,0201b; max speed, 100 m.p.h.; cruising speed, 90-95 m.p.h.; max rate of climb at $./., 1,330ft/min; hovering ceiling in ground effect, 6,000ft; range, 225 miles. Chance Vought Corporation PO Box 5907, Dallas 22, Texas XC-142A As joint winners in 1961 of an important design competition for a V/STOL transport for the US armed services, Chance Vought, Hiller and Ryan received a contract for five prototypes which are now taking shape as the XC-142A tilt-wing transport. Chance Vought is prime con tractor. Ryan is responsible for design and manufacture of the wings, rear fuselage, tail, engine mountings and nacelles. Hiller is designing and constructing the flaps, aile rons and complete power transmission. First flight is expected early in 1964. The XC-142A will be powered by four 2,850 s.h.p. General Electric T64-6 turbo- props, driving shafting linking the Hamilton Standard propellers, with glass-fibre blades, and the three-blade variable-pitch tail rotor. During VTOL operation, with the wing tilted vertically, roll control will be achieved by means of differential collective propeller pitch, yaw control by the ailerons in the propeller slipstream, and pitch control by the tail rotor. During transition, a mixing linkage will integrate this VTOL control system with the conventional control surfaces as a function of wing angle. Leading-edge flaps, outboard of each engine, will prevent stalling during trans ition by correcting for up-flow of the propeller slipstream. Main task of the production C-142 will t>e to transport combat troops, equipment ind supplies from assault ships or airfields Brant/y B-2A on pontoon floats into unprepared areas under all weather conditions. Payload will comprise either 32 fully-equipped troops or 8,0001b of freight, loaded via a ramp at the rear of the 30ft-long cabin. Span, 67ft 6in; overall length, 58ft f+in; height. 26ft I'm; VTOL gross weight, 42,5001b; STOL gross weight, 44,5001b; empty weight, 22,5951b; max speed, 409 m.p.h.; cruising speed, 288 m.p.h.; hovering ceiling out of ground effect, 6,000ft; max combat radius, 230 miles. Curtiss-Wright Corporation "Wood-Ridge, New Jersey X-19A This high-speed VTOL aircraft is designed to utilize four of Curtiss-Wright's Vought!Hiller/Ryan XC-I42A mock-up which everything is mounted. The under- slung engine is an 80 h.p. (derated to 56 h.p.) Kiekhaefer Mercury Model 800 flat-six, with belt drive to the three-blade main rotor and two-blade tail rotor. Conventional helicopter controls are fitted. There is no further news of the projected drone and T62-powered versions, but dur ing the past year both the DH-1 and GET-1 have been evaluated by US and foreign military and civil aviation authorities. Rotor diam, 16ft; length overall, 15ft I'm; height, 7ft; gross weight, 6001b; empty weight. 3801b; max speed, 74 m.p.h.; cruising speed, 45-55 m.p.h.; max rate of climb at s.l., 1,230ftjmin; service ceiling, 9,000ft; max range, 90 miles. "radial lift-force propellers." It has a tandem-wing layout, with the glass-fibre propellers (driven by two 2,200 s.h.p. Lycoming T55-L-5 turbines) rotated upward through 90° during VTOL. Curtiss-Wright claim that the propellers continue to develop a lift force when tilted down for forward flight, so that only very small fixed wings are required. Development of the X-19A (then known by the company designation of Model 200) was began as a private venture. As a first step, Curtiss-Wright built the X-100 twin- propeller research aircraft, illustrated in last year's survey. Its success confirmed their claims, and on July 17, 1962, they announced a USAF contract for construc tion and flight testing of two prototypes of the X-19A. The first is scheduled to fly this year and the aircraft will be evalu ated by all three Services. Span (across propeller blades). 34ft 6in; length of fuse lage, 43ft Sin; height, 16ft; gross weight, 12,3001b; max payload, 2,0001b; max speed, 460 m.p.h. Del Mar Engineering Laboratories International Airport, 6901 Imperial Highway, Los Angeles 45, California DH-1 Whirlymite During the past year, Del Mar have redesigned and "production ized" the DH-1 one-man helicopter and the associated GET-1 ground-cushion training device. The airframe remains a tubular and sheet-metal backbone on Doman Helicopters, Inc Municipal Airport, Danbury, Connecticut Doman -Ambrosini D-10B Attempts to get this helicopter into production over the past ten years have yet to bear fruit, but Doman report that airframes are being manufactured in Sicily by Aeronautica Sicula SpA. Final assembly, including installation of engines, rotor blades and instruments, will be performed by Doman in America, and it is hoped to fly the first production model next January. The D-10B is powered by a 400 h.p. Lycoming HIO- 720-A1 A, and features a hingeless rotor with totally-enclosed self-lubricating hub. It carries a pilot and either seven passengers, four stretchers and attendant, or 1,8101b of freight. Rotor diam, 48ft; fuselage length, 37ft lOin; height, 10ft 5in; gross weight, 5,5001b; empty weight, 3,3771b; max speed, 104 m.p.h.; cruising speed, 95 m.p.h.; max rate of climb at s.l., 840ftjmin; hovering ceiling in ground effect, 5,300ft; normal range, 322 miles. R. J. Enstrom Corporation Menominee County Airport, Michigan F-28 Enstrom suffered a setback last November 13, when the F-28 production prototype crashed. The second is being used for certification tests, due to be com pleted shortly, to permit initial deliveries by the end of the year. The F-28 is a side- by-side three-seater helicopter powered by a 180 h.p. Lycoming HO-360-A1A
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