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Gas Dynamics Laboratory
Gas Dynamics Laboratory (GDL) (Russian: Газодинамическая лаборатория) was the first Soviet research and development laboratory to focus on rocket technology. Its activities were initially devoted to the development of solid propellant rockets, which became the prototypes of missiles in the Katyusha rocket launcher, as well as liquid propellant rockets, which became the prototypes of Soviet rockets and spacecraft. At the end of 1933 it became part of the Reactive Scientific Research Institute (RNII). A number of craters on the far side of the Moon are named after GDL employees.
Nikolai Tikhomirov (1921—1930);
Boris Sergeevich Petropavlovsky (1930-1931);
Nikolai Yakovlevich Ilyin (rocket scientist) (1931—1932);
Ivan Kleymyonov (12.1932 - 9.1933, then head of the RNII).
The GDL utilised smokeless (TNT) gunpowder on a non-volatile solvent for solid propellant rockets. The first test-firing of a solid fuel rocket was carried out in March 1928, which flew for about 1,300 meters In 1931 the world's first successful use of rockets to assist take-off of aircraft were carried out on a U-1, the Soviet designation for an Avro 504 trainer, which achieved about one hundred successful assisted takeoffs. Successful assisted takeoffs were also achieved on the Tupolev TB-1 (Russian 'ТБ-1') and Tupolev TB-3 aircraft. Further developments in the early 1930s were led by Georgy Langemak, including firing rockets from aircraft and the ground. In 1932 in-air test firings of RS-82 missiles from a Tupolev I-4 aircraft armed with six launchers successfully took place. RNII then modified these rockets for the famous Katyusha rocket launcher, which were used during World War II. In these works, the main design contribution was made by GDL employees Nikolai Tikhomirov, Vladimir Artemyev, Boris Petropavlovsky, Georgy Langemak, Ivan Isidorovich and others.
On 15 May 1929 a section was created to develop electric rocket engines, headed by 23 year old Valentin Glushko, Glushko proposed to use energy in electric explosion of metals to create rocket propulsion. In the early 1930s the world's first example of an electrothermal rocket engine was created. This early work by GDL has been steadily carried on and electric rocket engines were used in the 1960s onboard the Voskhod 1 spacecraft and Zond-2 Venus probe.
In 1931 Glushko was redirected to work on liquid propellant rocket engines. This resulted in the creation of ORM (from "Experimental Rocket Motor" in Russian) engines ORM-1 to ORM-52. To increase the resource, various technical solutions were used: the jet nozzle had a spirally finned wall and was cooled by fuel components, curtain cooling was used for the combustion chamber and ceramic thermal insulation of the combustion chamber using zirconium dioxide. Nitric acid, solutions of nitric acid with nitrogen tetroxide, tetranitromethane, hypochloric acid and hydrogen peroxide were first proposed as an oxidizing agent. As a result of experiments, by the end of 1933, a high-boiling fuel from kerosene and nitric acid was selected as the most convenient in operation and industrial production. In 1931 self-igniting combustible and chemical ignition of fuel with gimbal engine suspension were proposed. For fuel supply in 1931-1932 fuel pumps operating from combustion chamber gases were developed. In 1933 a centrifugal turbopump unit for a rocket engine with a thrust of 3000 N was developed. A total of 100 bench tests of liquid-propellant rockets were conducted using various types of fuel, both low and high-boiling and thrust up to 300 kg was achieved.
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Gas Dynamics Laboratory
Gas Dynamics Laboratory (GDL) (Russian: Газодинамическая лаборатория) was the first Soviet research and development laboratory to focus on rocket technology. Its activities were initially devoted to the development of solid propellant rockets, which became the prototypes of missiles in the Katyusha rocket launcher, as well as liquid propellant rockets, which became the prototypes of Soviet rockets and spacecraft. At the end of 1933 it became part of the Reactive Scientific Research Institute (RNII). A number of craters on the far side of the Moon are named after GDL employees.
Nikolai Tikhomirov (1921—1930);
Boris Sergeevich Petropavlovsky (1930-1931);
Nikolai Yakovlevich Ilyin (rocket scientist) (1931—1932);
Ivan Kleymyonov (12.1932 - 9.1933, then head of the RNII).
The GDL utilised smokeless (TNT) gunpowder on a non-volatile solvent for solid propellant rockets. The first test-firing of a solid fuel rocket was carried out in March 1928, which flew for about 1,300 meters In 1931 the world's first successful use of rockets to assist take-off of aircraft were carried out on a U-1, the Soviet designation for an Avro 504 trainer, which achieved about one hundred successful assisted takeoffs. Successful assisted takeoffs were also achieved on the Tupolev TB-1 (Russian 'ТБ-1') and Tupolev TB-3 aircraft. Further developments in the early 1930s were led by Georgy Langemak, including firing rockets from aircraft and the ground. In 1932 in-air test firings of RS-82 missiles from a Tupolev I-4 aircraft armed with six launchers successfully took place. RNII then modified these rockets for the famous Katyusha rocket launcher, which were used during World War II. In these works, the main design contribution was made by GDL employees Nikolai Tikhomirov, Vladimir Artemyev, Boris Petropavlovsky, Georgy Langemak, Ivan Isidorovich and others.
On 15 May 1929 a section was created to develop electric rocket engines, headed by 23 year old Valentin Glushko, Glushko proposed to use energy in electric explosion of metals to create rocket propulsion. In the early 1930s the world's first example of an electrothermal rocket engine was created. This early work by GDL has been steadily carried on and electric rocket engines were used in the 1960s onboard the Voskhod 1 spacecraft and Zond-2 Venus probe.
In 1931 Glushko was redirected to work on liquid propellant rocket engines. This resulted in the creation of ORM (from "Experimental Rocket Motor" in Russian) engines ORM-1 to ORM-52. To increase the resource, various technical solutions were used: the jet nozzle had a spirally finned wall and was cooled by fuel components, curtain cooling was used for the combustion chamber and ceramic thermal insulation of the combustion chamber using zirconium dioxide. Nitric acid, solutions of nitric acid with nitrogen tetroxide, tetranitromethane, hypochloric acid and hydrogen peroxide were first proposed as an oxidizing agent. As a result of experiments, by the end of 1933, a high-boiling fuel from kerosene and nitric acid was selected as the most convenient in operation and industrial production. In 1931 self-igniting combustible and chemical ignition of fuel with gimbal engine suspension were proposed. For fuel supply in 1931-1932 fuel pumps operating from combustion chamber gases were developed. In 1933 a centrifugal turbopump unit for a rocket engine with a thrust of 3000 N was developed. A total of 100 bench tests of liquid-propellant rockets were conducted using various types of fuel, both low and high-boiling and thrust up to 300 kg was achieved.
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