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. 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). The new fighter (designated I-15ter by the design bureau and I-153 by the
Soviet Air Forces (VVS)) 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. 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) giving a much greater weight of fire. 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. 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. 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. 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. ==Operational history==