Review Article
Small Mars Mission Architecture Study
Table 4
Preliminary mass budget information for the Mars Communication Constellation mission.
| | | Mass (kg) |
| Attitude, orbit, guidance, navigation control | | 8.0 | Chemical propulsion | | 6.9 | Communication (UHF proximity link, DTE link: X-band, 50 W TWTA, 1 m HGA) | | 30.1 | Electric propulsion (T6 engine) | | 70.4 | Instruments | | 7.0 | Power (2.8 kW @Mars for electric propulsion) | | 158.9 | Structures | | 56.6 | Thermal control | | 13.3 | Data handling (0.5 Gb/day science data) | | 5.3 | Harness | | 17.8 | Dry mass | | 374.3 | System margin | 20% | 74.9 | Dry mass incl. system margin | | 449.2 | CPROP propellant mass | | 4.7 | CPROP propellant margin | 2% | 0.1 | EPROP fuel mass (10.4 km/s ΔV) | | 153.8 | EPROP fuel margin | 2% | 3.1 | Wet mass (per satellite) | | 610.9 | Constellation total dry mass incl. system margin | | 1347.6 | Constellation total wet mass | | 1832.7 | Launch adapter | | 360 | Launch mass (wet mass + adapter) | | 2192.7 |
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The bold values refer to summation values of the figures above them.
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