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Aviation History
1963
1963 - 1307.PDF
FLIGHT International, 25 July 1963 VTOL aircraft... 133 Agusta 204B Fiat G.95/4 model are based on the HA2O0 engine at the normal gross weight of 7,5001b. Max gross weight, 8,5001b; empty weight, 4,IO0lb; max speed, 138 m.p.h.; cruising speed, 124 m.p.h.; max rote of climb at s.l., 2,520ft]min; hovering ceiling out of ground effect, 11,000ft; normal range, 275 miles. Societa per Azioni Fiat Corso Giovanni Agnelli 200, Turin G.95/4 Although Fiat do not have a contract to build a prototype of this VTOL strike fighter, they have received a sub stantial research project contract from the Italian Air Force. This includes construc tion of an RB.108-powered flying rig of the kind built by Entwicklungsring Slid during development of the VJ 101C; Rolls-Royce are helping with its design and construction. In size and performance the G.95/4 comes between the Mach 1 P. 1127 and the Mach 2 Pi 154 and Mirage III-V. It is a mid-wing monoplane with four Rolls-Royce RB. 162-31 lift jets in the centre fuselage. Twin propulsion engines will probably be Rolls-Royce/MAN RB.153s with after burning. Gross weight has been estimated a s 15,000-17,0001b. G.222 Cervino Designed to meet Italian A >r Force requirements for a V/STOL transport, the G.222 is the subject of a research project contract similar to that awarded for the G.95/4. Its basic layout ls conventional, with fuselage-mounted Undercarriage and a loading ramp under tne upswept tail, but the short-span wings are characteristic of V/STOL aircraft. As envisaged at present, the G.222 would « powered by two 3,030-3,245 s.h.p. R oIls-Royce Dart turboprops in long nacelles that would each also house three ^B 162-31 lift jets. Such an installation would not permit VTOL operation at the gross weight of 35,0001b, but the G.222 would be able to reach 50ft in 650ft in a STOL take-off at full weight, and would land in the same distance. Vertical take-off would, of course, be possible at forward airstrips after fuel had been burned on the outward journey. Stabilization during VTOL and low-speed flight would be by a system of air-bleed jets. Typical payloads include 40 fully-equipped troops, 32 para troops, 24 stretcher cases or three jeeps, which could be carried 750 miles at 250 m.p.h. Development and possible production is planned as a programme involving most of the Italian aircraft industry, including the Aerfer, Aermacchi, Agusta, Piaggio and Siai-Marchetti companies, as well as Fiat and Finmeccanica who were jointly respon sible for the project. Conte Ettore Manzolini di Campoleone Via Francesco Siacci 4, Rome Libellula II The extensive programme of test flying and refinement to which this single-seat light helicopter has been sub jected had its reward on October 15, 1962, when the prototype was certificated by the Registro Aeronautico Italiano. In its fully- developed form, it has a conventional uncovered steel-tube fuselage structure, an enclosed cabin and a skid undercarriage. The co-axial two-blade rotors are driven by a 101 h.p. Walter Minor 4-III piston engine. Rotor diam, 29ft bin; length of fuselage, 15ft I lin; height, /0ft 0±in; gross weight, /,4331b; empty weight, l,095lb; max speed, 68 m.p.h.; cruising speed, 56 m.p.h.; max rate of climb at s.l., 780ft[min; max range, 125 miles. Libellula HI This side-by-side two-seat helicopter is slightly larger than the Libel lula II and is powered by a 140 h.p. M332 in-line engine. Four prototypes are being built, and the first should fly before the end of the year. A four-seat version, known as the Libellula IV, with two 145 h.p. Rolls- Royce/Continental O-300 engines, is in the advanced design stage. Rotor diam, 32ft (Oin; length of fuselage, 16ft 5in; height, I Oft 7 in; gross weight, 1,8751b; empty weight, 1,4331b; max speed, 87 m.p.h.; cruising speed, 62 m.p.h.; max rate of climb at s.l., 985ftlmin; max range, 155 miles. SM-1WS Poland) POLAND Motoimport Przemyslowa 26, Warsaw SM-1 Although the Soviet Union sent no aircraft to this year's Paris Salon, the Polish industry demonstrated an SM-1WS, which is a licence-built version of the Russian Mi-1 helicopter. Although laden with two external stretcher panniers, it put up a very spirited performance and left little doubt of the quality of Mikhail Mil's designs. Production of the basic SM-1 began at the WSK Zygmunta Pulawskiego at Swidnik in 1955. It was superseded in 1960 by the much-improved SM-1W series, which has been manufactured in large numbers for home and export. The standard SM-1W accommodates a pilot and three passengers. With stretcher panniers and medical equipment installed it becomes the SM-1 WS; the SM-1WZ is an agricultural dusting and spraying version, and the SM-1 WSZ a dual- control trainer. All have a 575 h.p. LiT-3 (Polish-built AI-26V) seven-cylinder fan- cooled radial. Rotor diam, 46ft I tin; length of fuselage, 39ft 5in; height, 10ft Win; gross weight, 5,3001b; empty weight, 4,1421b; max speed, 105 m.p.h.; max rate of climb at s.l., 886ft) min; service ceiling, 9,840ft; range (with auxiliary tank age), 360 miles. SM-2 First flown in the summer of 1960, the SM-2 was developed at the WSK Swidnik to take full advantage of the pay- load potential of the basic Mi-1 design. It has a completely new front fuselage and structural modifications to permit the carriage of five persons. The cabin is long enough to accommodate two stretchers internally, loaded through a sideways- hinged door in the starboard side of the nose. An agricultural version is also available. Deliveries began in early 1961. Rotor diam, 47ft lin; length of fuselage, 39ft 8in; height, 10ft I Oin; gross weight. 5.4961b; empty weight, 4,1661b; max speed, 105 m.p.h.; cruising speed, 81 m.p.h.; max rate of climb at s.l., 886ft/min; service ceiling, 13, /20ft; normal range, 190 miles; range with auxiliary tankage, 310 miles.
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