AIM spacecraft Facts & Figures
The baseline propulsion system for the AIM spacecraft will use a bi-propellant (MMH/MON) fuel with 24 thrusters, each capable of producing 10 N of thrust.
A separate Helium tank would keep the four 60 L propellant tanks pressurized. Power is generated by two deployable, fixed solar arrays with an output of 165 W each at a distance of 2.2 AU from the Sun, and a total panel surface of 5.6 m². The total spacecraft dry mass would be about 420 kg and the propellant mass about 292 kg.
Spacecraft mass budget under study
| Subsystem |
Mass [kg] |
Margin [kg] |
Mass with Margin [kg] |
| Structure | 63.27 | 11.95 | 75.22 |
| Thermal control | 7.60 | 0.71 | 8.31 |
| Communications | 14.40 | 1.74 | 16.14 |
| Data handling | 17.30 | 1.48 | 18.78 |
| GNC | 26.26 | 1.36 | 27.62 |
| Propulsion | 65.62 | 3.22 | 68.84 |
| Power | 38.60 | 2.13 | 40.73 |
| Solar array wing (2) | 19.60 | 0.98 | 20.58 |
| Battery | 4.00 | 0.40 | 4.40 |
| PCDU | 15.00 | 0.75 | 15.75 |
| Instruments | 63.55 | 10.85 | 74.40 |
| VIS camera | 2.20 | 0.22 | 2.42 |
| Thermal infrared Imager (TIRI) | 3.30 | 0.33 | 3.63 |
| Monostatic high-frequency radar (HFR) | 1.40 | 0.28 | 1.68 |
| Bistatic low-frequency radar (LFR) | 1.10 | 0.11 | 1.21 |
| OPTEL-D | 32.75 | 6.55 | 39.30 |
| MASCOT-2 | 10.80 | 2.16 | 12.96 |
| Cubesats (incl. deployer) | 12.00 | 1.20 | 13.20 |
| Harness | 20.00 | 0.00 | 20.00 |
| Dry mass | 316.60 | 350.03 | |
| System Margin | 20% | ||
| Total dry mass with margin | 420.04 kg | ||
| Propellant | 292.00 kg | ||
| Total wet mass with margin | 712.00 kg | ||
| Launch mass (incl. adapter) | 822.04 kg | ||