Statistics – Applications
Scientific paper
Oct 2004
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2004esasp.555e..77a&link_type=abstract
Proceedings of the 4th International Spacecraft Propulsion Conference (ESA SP-555). 2-9 June, 2004, Chia Laguna (Cagliari), Sard
Statistics
Applications
Scientific paper
Paper presents the estimate of Ablative Pulsed Plasma Thruster (APPT) models for LEO applications. The models developed in RIAME within last decade cover 20- 150 J bank energy range. These have high efficiency and are attractive onboard EP option for Small Spacecrafts (SSC) due to their simplicity, low mass, appropriate power level, high Isp and low cost. Main characteristics of modern high thrust efficiency APPT developed in Russia with the bank energy range 20- 150 J are presented. The threat of contamination of SSC and its functional instrumentation is tested. It is observed that decreasing of an integral transparency of optical devices in visible area of a spectrum during APPT service life will not exceed 2.5 % that much lower than effect of space factors. Inductive electromagnetic disturbances also have not dangerous value. SSO orbits from 500 to 900 km and SSC with mass 100-350 kg are considered. For LEO applications PPT technology shows the high competitiveness between other small propulsion systems developed for SSC orbit control (translational maneuvers, orbit maintenance and positioning). Accounts of total impulse, propulsion system mass and propellant consumption for producing all types of orbit maneuvers for SSCs, having 7 - 10 years service life, are presented for a number of missions. The use of APPT in the spacecraft control systems were assessed for a heavy spacecraft of 2 500 kg in mass. PPT based propulsion system for a heavy spacecraft attitude control allows substantial savings in the total impulse and propulsion system mass.
Antropov N.N.
Kazeev M.
Khodnenko V.
Popov Gennadiy
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