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.
The paper presents studies conducted at RSC Energia that looked into the feasibility of developing a high-temperature high-power voltage converter of a low-voltage space power supply system for an electrically-propelled space transportation spacecraft based on classical voltage conversion systems using electroplasma gates (key elements) and high-temperature transformers. It provides electrical schematics fro voltage conversion systems. It presents results of experimental studies on lab prototypes of electroplasma gates with electrical power of tens and hundreds kilowatts, which have demonstrated that in principle it is possible to use them as a basis for development of high-temperature radiation-proof voltage converters with mass fraction of ~0.01 kg/A for such power sources as nuclear power-supply systems with sub-megawatt and megawatt thermionic converter reactor. It provides a rationale for selecting the voltage conversion frequency in systems without forced cooling. It provides an experimental proof that in principle it is possible to implement high-temperature transformers with 600°С operating temperature level, and gives recommendations on selection of materials.
Key words: Space power system, electrically-propelled transportation spacecraft, voltage converter, electroplasma gate, high-temperature transformer, conversion frequency.
The paper presents results of conceptual design studies to determine configuration of an electrically propelled upper stage (EPUS) – a space transportation stage (a space tug) with main engines based on electric propulsion powered by solar arrays. It addresses the problem of deploying a multi-plane orbital constellation of small spacecraft (SSC) using an electrically propelled upper stage. It proposes to change the SSC operational orbital planes based on the effect of the difference in precession rates between the parking and the working orbits owing to the effect of eccentricity in the Earth gravitational field. Requirements have been defined for the EPUS electrical propulsion system that take into account the need to operate it to offset the aerodynamic drag while waiting in the parking orbit for the SSC operational orbital plane to turn.
It demonstrates the feasibility of employing four EPUS that use Stationary Plasma Thruster-type electric propulsion as their main engines and gallium arsenide solar arrays for deployment in a 600 km orbit in four planes an orbital constellation of 24 small spacecraft with a mass of ~250 kg each using one launch of a medium capacity launch vehicle of Soyuz-2.1b type.
Key words: Electrically propelled upper stage, electric propulsion, small spacecraft, orbital constellation.
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