75th anniversary of S.P. Korolev Rocket and Space Corporation Energia

Author(s):  
Vladimir SOLOVIEV ◽  
◽  
Mikhail RESHETNIKOV ◽  
Viktor SINYAVSKIY

The article briefly discusses the key achievements of the enterprise over 75 years from the formation of OKB-1 headed by S.P. Korolev for producing intercontinental range missiles to the current status of RSC Energia being the country’s and world leader in manned space flight. The developed intercontinental missiles R-7 and a closed-loop oxygen-hydrocarbon liquid-propellant rocket engine provided the basis for developing integrated launch vehicles which were used to launch the world’s first Earth satellite, the first cosmonaut on the Earth, automatic interplanetary stations to the Moon, Venus, Mars. The diversification of the enterprise impeded S.P. Korolev to concentrate on manned space flights, and he initiated the transfer of development and manufacture of combat missiles to V.P. Makeev DB, integrated launch vehicles to TsSKB Progress, communication and other satellites to M.F. Reshetnev ISS, lunar and interplanetary stations to S.A. Lavochkin NPO. In the 1980s under the guidance of V.P. Glushko the Energia super-heavy launch vehicle and Energia–Buran system in unmanned configuration were developed and successfully launched on the first try. The Salyut manned single-module orbital stations, Mir multifunctional multi-module space laboratory and successfully operating upgraded manned transportation (Soyuz) and logistics (Progress) spacecraft were developed. In the hard times of 1990s, RSC Energia under the guidance of Yu.P. Semenov saved the national cosmonautics through commercial research performed on the Mir station. At present, RSC Energia together with Khrunichev Space Center is completing the stage of ground tests of a multipurpose laboratory module and is manufacturing modules for a promising near-Earth manned station.

Author(s):  
Vladimir A. SOLOVIEV ◽  
RESHETNIKOV Mikhail N. RESHETNIKOV Mikhail N ◽  
Viktor V. SINYAVSKIY ◽  
Sergey Yu. SHACHNEV

The article briefly discusses the key achievements of the enterprise over 75 years from the formation of OKB-1 headed by S.P. Korolev for producing intercontinental range missiles to the current status of RSC Energia being the country’s and world leader in manned space flight. The developed intercontinental missiles R-7 and a closed-loop oxygen-hydrocarbon liquid-propellant rocket engine provided the basis for developing integrated launch vehicles which were used to launch the world's first Earth satellite, the first cosmonaut on the Earth, automatic interplanetary stations to the Moon, Venus, Mars. The diversification of the enterprise impeded S.P. Korolev to concentrate on manned space flights, and he initiated the transfer of development and manufacture of combat missiles to Makeyev DB, integrated launch vehicles to TsSKB Progress, communication and other satellites to M.F. Reshetnev ISS, lunar and interplanetary stations to S.A.Lavochkin NPO. In the 1980s under the guidance of V.P. Glushko the Energia super-heavy launch vehicle and Energia-Buran system in unmanned configuration were developed and successfully launched on the first try. The Salyut manned single-module orbital stations, Mir multifunctional multi-module space laboratory and successfully operating upgraded manned transportation (Soyuz) and logistics (Progress) spacecraft were developed. In the hard times of 1990s, RSC Energia under the guidance of Yu.P. Semenov saved the national cosmonautics through commercial research performed on the Mir station. At present, by launching three additional modules RSC Energia is completing assembly and integration of the Russian Segment into the International Space Station. Keywords. ОKB-1, S.P.Korolev RSC Energia, V.P. Glushko, Yu.S. Semenov, integrated launch vehicle, orbital station, crew transportation spacecraft, logistics transportation spacecraft, International Space Station.


2018 ◽  
Vol 2018 ◽  
pp. 1-14
Author(s):  
Jiang Chang ◽  
Gongping Wu ◽  
Hanwei Tang

Based on relative theories of gas dynamics and computational fluid dynamics, the flow field computation software ANSYS Fluent was used to simulate the steady flow field of the solid type ignition device of liquid-propellant rocket engine in two working conditions (condition I: without ignition channel, condition II: with ignition channel). On this basis, the influence of ignition channel on the working characteristics of the solid type ignition device of the liquid-propellant rocket engine was analyzed and experimentally tested. The results showed that when the pressure in the combustion chamber was atmospheric pressure, under condition II, the gas velocity at the throat of the ignition device did not reach the sonic velocity, and the position of sonic velocity moved to the downstream section of the ignition channel. Compared to condition I, the gas velocity and energy at the ignition outlet increased, which would be beneficial for initial ignition, and the gas pressure and temperature at the throat increased as well, indicating that the structural strength at the throat should be evaluated. The gas flow, gas pressure, and gas temperature at the ignition outlet decreased compared to working condition I, yet the changes were small and would have minimal effect on the ignition performance. During the pressure increase process in the combustion chamber, the gas pressure, velocity, temperature, flow, and energy at the ignition outlet experienced a steady stage in both working conditions before coming to an inflection point. The inflection point under condition II is smaller than that under condition I. To improve the ignition reliability, the working pressure of the ignition device should be further increased.


Author(s):  
M. M. Dron ◽  
◽  
A. B. Yakovlev ◽  

The quality of the flight task of a space rocket system is determined among other things by the accuracy of maintaining and regulating the thrust of the rocket engine. Improving the accuracy and reducing errors in the engine mode control system will reduce the cost of space launches or allow you to put a large payload into orbit. The article presents a mathematical model of a controller with an inertial booster of a liquid-propellant rocket engine, identifies parameters and values that affect its accuracy, and considers measures to reduce static error


2010 ◽  
Vol 26 (5) ◽  
pp. 897-923 ◽  
Author(s):  
Matthew J. Casiano ◽  
James R. Hulka ◽  
Vigor Yang

Aerospace ◽  
2019 ◽  
Vol 6 (12) ◽  
pp. 129 ◽  
Author(s):  
Igor Borovik ◽  
Evgeniy Strokach ◽  
Alexander Kozlov ◽  
Valeriy Gaponov ◽  
Vladimir Chvanov ◽  
...  

The combustion of kerosene with the polymer additive polyisobutylene (PIB) was experimentally investigated. The aim of the study was to measure the effect of PIB kerosene on the efficiency of combustion chamber cooling and the combustion efficiency of the liquid propellant for a rocket engine operating on kerosene and gaseous oxygen (GOX). The study was conducted on an experimental rocket engine using kerosene wall film cooling in the combustion chamber. Fire tests showed that the addition of polyisobutylene to kerosene had no significant effect on the combustion efficiency. However, analysis of the wall temperature measurement results showed that the use of PIB kerosene is more effective for film cooling than pure kerosene, which can increase the efficiency of combustion chamber cooling and subsequently increase its reliability and reusability. Thus, the findings of this study are expected to be of use in further investigations of wall film cooling efficiency.


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