The “CHUR No.1” aircraft was named after its creators: Chechet, Ushkov, and Rebikov. Its main constructor was engineer Nikolai Vasilyevich Rebikov, a well-known figure in Russian aviation at the time. M.K. Ushkov, a wealthy Muscovite, financed its construction, which began on the initiative of its inventor, Grigory Gerasimovich Chechet. The manufacturing took place in 1911 in a private workshop in Saint Petersburg.
From March 25 to April 8, 1912, the aircraft was exhibited in Moscow at the 2nd Aeronautical Exhibition. Subsequently, the CHUR No.1 underwent testing at the Komendantsky Airfield, also in Saint Petersburg.
Conception and Design Anomalies
The CHUR No.1’s design reflected some misconceptions characteristic of the 1910-1911 period. It was a braced monoplane with an additional wing surface, acting somewhat like an inverse sesquiplane. It featured a conventional fuselage, a tractor power plant, and a biplane tail assembly.
Powered by a 100 hp “Argus” engine, the main wing lacked ailerons or wing warping. However, bifurcated surfaces were placed at its tips, angled at 90 degrees, to prevent slipping. The upper plane could change its angle of incidence in flight and carried ailerons placed obliquely on its leading edge, deflectable upwards by up to 30 degrees. During testing, ailerons were also added to the lower wing.
Structural Innovations and Unique Features
The fuselage featured a quadrangular front section, constructed from steel pipes using autogenous welding, a first in Russia. The rear section was triangular, made of braced wood and reinforced with aluminum cups. The fuselage was covered along its entire length.
The landing gear had wooden struts of equal resistance, meaning they tapered towards their ends. An additional surface was added above the triangular stabilizer, capable of changing its angle of incidence in flight to eliminate stick forces.
Operational History and Fate
Nikolai V. Rebikov’s flights in this aircraft concluded with an accident on July 5, 1912. Following this incident, the CHUR No.1 was not restored, bringing its short history to an end.
Technical Specifications
| Modification | CHUR No.1 |
| Wingspan, m | 14.00 |
| Length, m | 11.00 |
| Wing area, m2 | 36.00 |
| Empty weight | 600 |
| Maximum takeoff weight | 700 |
| Engine type | 1 Piston engine Argus |
| Power, hp | 1 x 100 |
| Crew | 1 crew member |
Image and diagram gallery of the CHUR No.1
 CHUR No.1 |
 CHUR No.1 |
 CHUR No.1 |