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    • The analysis of transport opportunities of an oxygen-hydrogen chemical upper stage at insertion into a geostationary orbit for space system on the basis of a launcher Soyuz 2-1b

    Paper number

    IAC-06-D2.3.10

    Author

    Prof. Mikhail S. Konstantinov, Moscow Aviation Institute (MAI), Russia

    Coauthor

    Mr. Mark Skryabin, Russia

    Year

    2006

    Abstract
    Transport operation of a satellite insertion into a geostationary orbit (GEO) is examined. The space transport system on the basis of a launcher Soyuz 2-1b is analyzed. The comparative analysis of transport opportunities of several types of chemical upper stages is carried out.
The following chemical upper stages are analyzed: Fregat SB; an oxygen-kerosene upper stage (thrust 2000g N, specific impulse 349g m/s); an oxygen-methane upper stage (thrust 2000g N, specific impulse 370g m/s); and an oxygen-hydrogen upper stage (thrust 2000g N or 1000g N, specific impulse 455g m/s). The basic idea is to show a ballistic opportunity and advantages of use of the oxygen-hydrogen upper stage created on the basis of modified steering chambers of the engine of the Indian upper stage. Two variants of propulsion are considered. It is shown, that use of four-chamber engine (on the basis of four modified steering chambers) enables to use a upper stage for spacecraft inserting into a low circular orbit (LEO) and then to provide inserting into a geostationary orbit a spacecraft of the big mass. So at use of the cosmodrome Baikonur the mass of a spacecraft in GEO is more than 1800 kg.
The analysis of characteristics of transport system is spent for following entrance data. It is considered, the launcher Soyuz 2-1b at start from cosmodrome Baikonur inserts the head block of mass 10000 kg into not closed ballistic orbit. The height of apogee of an orbit is little bit more 209 km. Its perigee is located inside of the Earth (height of a perigee a minus of 924 km). An orbit inclination is equal to 51.4 degrees.
Results of the preliminary design-ballistic analysis are presented below:
ChUS Fregat SB - terminal mass of the head block 1810 kg; terminal mass of the chemical upper stage 950 kg; Mass of SC in GEO 860 kg.
Oxygen + kerosene ChUS - 2150 kg; 1000 kg; 1150 kg.
Oxygen + hydrogen ChUS - 2300 kg;  800 kg; 1500 kg.
Oxygen + methane ChUS - 3050 kg; 1250 kg; 1800 kg (for thrust 2000g N).
Oxygen + methane ChUS - 3000 kg; 1150 kg; 1850 kg (for thrust 1000g N).
The engine of oxygen-hydrogen upper stage is being fired four times. The first starting provides SC transfer into LEO with height of 209 km. SC mass in this orbit is 9167 kg. The second starting of this engine provides SC transfer into the first intermediate orbit. Height of its apogee is 8159 km, height of a perigee - 390 km, an inclination - 49.7 degrees.
The third starting of the engine provides flight into GTO. Height of a perigee of this orbit is 466.4 km. An inclination is 48.6 degrees. SC mass in this orbit is equal to 5134.7 kg. Last inclusion of the engine provides SC inserting into a geostationary orbit. SC mass in GEO is a little more 3000 kg.
    Abstract document

    IAC-06-D2.3.10.pdf

    Manuscript document

    IAC-06-D2.3.10.pdf (🔒 authorized access only).

    To get the manuscript, please contact IAF Secretariat.