Here is some data of the space stations designed by the two design teams of SSDW IRS 2001.

Each team had to design a minimum-configuration space station that could support the preparation of crew and technologies for the first human mission to Mars. Additionally, during the assembly phase of the station, opportunities for microgravity experiments and space science were to be provided.
The students used a modified SSDW methodology, and SSDW tools like IRIS and ELISSA, to design and analyze their stations.

The following results are available:

Blue Team

System Concept:

• Crew: permanent, 3 for maintenance/experiments, 4 for Mars mission preparation/training
• Orbit: circular, 300-350 km (during assembly) to 450-500 km (assembly complete), inclination 30.2°
• Flight Mode: earth-oriented, gravity-gradient stabilized (TEA 12.3°, partially continous reboost (Arcjet fed by H2 from ECLSS)
• Impulsive reboost (option for ECLSS waste-fed CO2 resistojet for permanent reboost or CMG desaturation)
• Launchers:
  • assembly: STS, Proton, Ariane 5E
  • resupply: ATV
  • crew transport: CTV, Soyuz (STS)

Space Segment Description:

1 Core module (modif. ISS-FGB)
1 Lab (ISS-JEM with cupola, robotic arm and external facility)
1 Hab (ISS-US Hab)
1 Inflatable Mars training module (Konopek Sphere)
2 Nodes (ISS-Node 2)
1 Airlock (ISS-US Airlock)
1 CRV docking adapter
1 CRV
1 Shuttle docking adapter (Mir)
1 Soyuz
1 ATV
2 Truss with photovoltaic arrays and radiators

Assembly Sequence

ECLSS Design and Simulation:

Click on picture on right for ELISSA simulation model of ECLSS

Major ECLSS components:

• Water loop: TIMES and Multifiltration
• Air loop: Four-Bed Molecular Sieves,
  Sabatier, Electrolysis, ACRS;
  simulation results for Oxygen

Human Factors Issues:

Green Team

System Concept:

• Crew: permanent, 3 to 8 (during changeover)
• Orbit: circular, 385-400 km
• Flight Mode: earth-oriented, gravity-gradient stabilized (TEA 2°, impulsive reboost every 92 days)
• Impulsive reboost every 65 days
• 650 m² of solar arrays installed for 51 kW permanent EPS output
• Launchers:
  • assembly: STS, H-IIA, Ariane 5E
  • resupply: Progress, ATV (Ariane 5)
  • crew transport: Soyuz (STS)

Space Segment Description:

1 Core module (modif. JEM)
1 Laboratory (modif. ISS-COF, with external facility)
1 Habitation module (modif. Spacelab)
1 Mars training module (modif. and extended JEM)
2 Nodes (ISS-Node 1 and ISS-Node 2)
1 Airlock (ISS-US Airlock)
1 CRV docking adapter
1 CRV
2 Truss with photovoltaic arrays and radiators

Assembly Sequence

AOCS Design and Simulation:

Altitude envelope (min./max.) 385 - 400 km
Inertia tensor [10E6 kg m²]:

	17.42   	 0.00124	 0.00
	 0.00   	14.42   	 0.18
	 0.00   	 0.00   	 7.62

Drag incidence surface area (min./max.) 600 m² / 1000 m²
Center of mass (x/y/z) w/r/t central node: 0.036 m / 0.203 m / 5.55 m
Propellant needs (impuls. reboost / attitude) 502 kg/yr 
Attitude performance: TEA 2°
Reboost cycle period 92 days

Configuration Alternatives:

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