Abstract
The design-and-ballistic analysis of Phobos Sample Return Mission has been carried out. The principle objective of the mission is a soil-sample delivery from Mars’s satellite Phobos to the Earth. The project is scheduled for the period of 2007-2010 to be implemented. The 8120 kg-SC insertions into 200 km orbit is carried out by a “Soyuz”type launch vehicle (LV). The 3-stage rocket engine system is installed at S/C. The thrust and specific impulse of the first stage-liquid engine are about 2 ton and 330 sec, respectively. The second stage is the electric propulsion subsystem (EPS) consisting of three 4,5 kW-SPT-140 thrusters. The liquid engine of the third stage develops 50 kg of thrust at 312 sec of specific impulse. EPS application changes strongly the mission strategy and spacecraft design configuration. The Si-solar array develops 9000 W in the near-Earth orbit (and expected 3416 W in the Mars vicinity) from which 7500 W is used for the EPS supplying. The paper describes and discusses the highlights of the design-and-ballistic analysis of the all mission stages as well as technical SC parameters.
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