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    Engineering

    Table of Facts

    Table 1: Launcher statistics

    Launcher

    Launcher Capability

    Soyuz-Fregat

    1060 kg

    Delta II

    1100 kg

    S/C Item

    Current Mass

    Spacecraft Bus

    439 kg

    Lander

    60 kg

    Payload

    116 kg

    Propellant

    427 kg

    Launch Mass

    1042 kg

    Typical Mean Power Demand

    Observation

    Manoeuvre

    Communication

    Spacecraft

    270 W

    310 W

    445 W

    Payload

    140 W

    50 W

    55 W

    Total

    410 W

    360 W

    500 W

    Table 2: General facts and figures

    Spacecraft bus dimensions

    1.5×1.8×1.4 m

    Thrust of main spacecraft engine

    400 N

    Attitude thrusters

    8 at 10 N each

    Propellant

    267 litres

    Pointing performance

    0.15°

    Table 3: Power supply

    Solar array area

    11.42 m²

    Lithium batteries

    3 at 22.5 Ah each

    Table 4: Temperature requirements and thermal specification

    Spacecraft bus

    +10-20 °C

    PFS, Omega

    -180 °C

    Thermal blanket

    Gold-plated AISn alloy

    Surface radiator

    		  

    Thermal Control

    Last Update: 01 Dec 2009

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