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The Russian Polikarpov I-153 ''Chaika'' (Russian ''Чайка'', "Seagull") was a late 1930s Soviet biplane fighter. Developed as an advanced version of the I-15 with a retractable undercarriage, the I-153 fought in the Soviet-Japanese combats in Mongolia and was one of the Soviets' major fighter types in the early years of the Second World War. It set several records, including the world air speed record for biplanes, still not beaten today. ==Design and development== In 1937, the Polikarpov design bureau carried out studies to improve on the performance of its I-15 and I-15bis biplane fighters without sacrificing manoeuvrability, as Soviet tactical doctrine was based on a mix of high performance monoplane fighters (met by the Polikarpov I-16) and agile biplanes.〔Gordon and Dexter 1999, p. 124.〕 Early combat experience from the Spanish Civil War had shown that the I-16 had problems dealing with the Fiat CR.32 biplanes used by the Italian forces supporting the Nationalists, which suggested a need to continue the use of biplane fighters, and as a result, Polikarpov's proposals were accepted, and his design bureau was instructed to design a new biplane fighter. Polikarpov assigned the task to the design team led by Aleksei Ya Shcherbakov, who was assisted by Artem Mikoyan and Mikhail Gurevich (who would later set up the MiG design bureau).〔Green and Swanborough 1979, p. 24.〕 The new fighter (designated I-15ter by the design bureau and I-153 by the Soviet Air Forces (VVS)〔Gordon and Dexter 2002, p. 79.〕) was based closely on the design of the I-15bis, with a stronger structure, but was fitted with a manually retractable undercarriage to reduce drag. It reverted to the "gulled" upper wing of the original I-15 but used the Clark YH aerofoil of the I-15bis.〔Green and Swanborough 1979, p. 25.〕 The four 7.62 mm PV-1 machine guns of the I-15bis were replaced by four ShKAS machine guns. While still rifle-calibre weapons, these fired much faster than the PV-1s, (1,800 rounds per minute rather than 750 rounds per minute〔Gordon and Dexter 2002, pp. 82–83.〕) giving a much greater weight of fire.〔 The new fighter was to be powered by a Shvetsov M-62 an improved derivative of the Shvetsov M-25 that powered the I-15 and I-15bis with twin superchargers.〔Gordon and Dexter 2002, pp. 79, 81.〕 The aircraft was of mixed metal and wood construction, with the fuselage structure being based on chromium-molybdenum steel with duralumin skinning on the forward fuselage, and fabric covering on the fuselage aft of the front of the cockpit. The aircraft's wings were made of fabric covered wood, while the tail surfaces were of fabric covered duralumin.〔Green 1971, p. 11.〕 The aircraft was fitted with a tailwheel undercarriage, with the mainwheels retracting rearwards, rotating through 90 degrees to lie flat in the wing roots, being actuated by cables operated by a pilot-driven handwheel. The solid rubber tailwheel did not retract, but moved in conjunction with the rudder.〔 The M-62 was not ready by the time the first prototype was complete, so it was fitted with a 750 hp (560 kW) M-25V engine when it made its maiden flight in August 1938.〔 The first prototype failed factory testing due to numerous defects, but this did not stop production, with the aircraft entering production concurrently with ongoing testing and development. Early production I-153s powered by the M25 engine passed state testing during 1939, despite the loss of one aircraft which disintegrated in a 500 km/h (311 mph) dive. In test flights, the I-153 (M-25) achieved the top speed of 424 km/h (264 mph), service ceiling of 8,700 m (28,500 ft), and required 6 minutes 24 seconds to reach 5,000 m (16,404 ft).〔 This performance was well in excess of that demonstrated by the I-15bis.〔 During 1939, production switched to a version powered by the originally planned M-62 engine, with an M-62 powered prototype undergoing state testing from 16 June 1939. While speed at sea level was virtually unchanged, the new engine improved performance at altitude.〔Green and Swanborough 1979, p. 26.〕 A speed of 443 km/h (275 mph) at 4,600 m (15,100 ft) was recorded, with a service ceiling of 9,800 m (32,100 ft). This performance was disappointing, and caused the aircraft to fail the state acceptance trials, although this did not disrupt production.〔Gordon and Dexter 2002, p. 81.〕 While it was recognised that the I-153's performance was inadequate, the over-riding requirement was to not disrupt production until more advanced fighters could enter production.〔 While numerous improvements were proposed, many were too radical to be implemented since the aircraft was already in production. Desperate to improve performance, Polikarpov tested two I-153 with the Shvetsov M-63 engine with 820 kW (1,100 hp). However, the results were disappointing and it was becoming painfully obvious that the biplane airframe was incapable of higher speeds. One of the rarely mentioned characteristics of the I-153 was its poor performance in a spin. While the Polikarpov I-16 had gained notoriety for entering spins, pilots found it easy to recover from a spin. In contrast, while the I-153 was difficult to spin, once it lost control, recovery was difficult to the point where intentional spinning was forbidden for some time. A spin recovery procedure was eventually developed but, while effective, it required flawless timing and execution. By the end of production in 1941, a total of 3,437 I-153s were built. 抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』 ■ウィキペディアで「Polikarpov I-153」の詳細全文を読む スポンサード リンク
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