Tupolev I-4
The Tupolev I-4, (Russian Туполев И -4), also known as ANT -5 ( АНТ -5 ) refers, was a single-engine, single-seat sesquiplane. It was developed in the second half of the 1920s and stood as a fighter until 1938 when the Soviet air forces in action.
Development
Responsible for the construction was Pavel Sukhoi, head of a development team of AGOS, a special unit of TsAGI, which was under Andrei Tupolev.
Two prototypes were built, the first one with a Jupiter VI, the second with a Jupiter IV engine, both from the French manufacturer Gnôme -Rhône. In July 1927, the first flight of the model took place and after the end of state testing decision was made in December of the same year, to give the aircraft into production. Before this began on October 25, 1928, some changes on the tail were still made. In the course of production is moved from Jupiter engine for Soviet License Type M - 22nd
The series production ended in 1934 after 371 machines. They came in the fighter squadrons, and after 1938 at the training sessions used. There were even tested some special versions, so in 1931 I- 4a without the lower sash as well as leading edge slats on the upper wing. The 1929 used for the Sweno piggyback project I-4 shortened to the lower wing on each side by 0.5 m. In another airplane experimented with an attached on the upper wing machine gun, some machines were equipped with two 7.62 -inch guns Kurschewski DRP / APK mounted on the upper wing.
1932, with an I -4 for the first time by the gas dynamic laboratory ( GDL) developed 82 -mm rockets tested. After fusion of the GDL with the Rocket Research Institute ( RNII ) the experiments were continued in 1935; from them emerged the Katyusha missiles.
A planned float version I- 4P 1931 was abandoned.
Description
The I-4 was constructed entirely in all-metal construction, the panel consisted of corrugated Duralblech. The two-piece upper wing had three spars, was mounted on a strut bracket and secured with two struts bands on the fuselage and two V- stems on extremely short lower wing. The profile thickness was in the struts 16 and 12 % at the ends. The rigid chassis had a solid axle and a tail skid.