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

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