Institutsleiter

Prof. Dr.-Ing.
Stefanos Fasoulas

Stellvertreter

Prof. Dr.-Ing. Sabine Klinkner

Prof. Dr. rer. nat. Alfred Krabbe

Sekretariat
Prof. Fasoulas

Sheyla Fröhler-Valdez

Sekretariat
Prof. Klinkner

Annegret Möller

Sekretariat
Prof. Krabbe

Barbara Klett

Administration

Dr. Thomas Wegmann

 


Institut für Raumfahrtsysteme
Pfaffenwaldring 29
70569 Stuttgart

Tel. +49 711 685-69604
Fax +49 711 685-63596

Direkt zu

 


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
  • Space Segment Description
  • Assembly Sequence
  • ECLSS Design and Simulation
  • Human Factors Issues
Green Team
  • System Concept
  • Space Segment Description
  • Assembly Sequence
  • AOCS Design and Simulation
  • Configuration Alternatives
VRML model VRML model
(software or browser plugin necessary for the VRML models)


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

slide1.png (1345 Byte) slide2.png (3042 Byte) slide3.png (3320 Byte)
slide4.png (3809 Byte) slide5.png (3828 Byte) slide6.png (3442 Byte)
slide7.png (5015 Byte) slide8.png (3610 Byte) slide9.png (4411 Byte)
slide10.png (5650 Byte) slide11.png (5495 Byte) click here to see the VRML model

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:

Habitation Module Zoning Mars Training Module Internal Layout

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

step1.jpg (127964 Byte) step2-3.jpg (171298 Byte) step4.jpg (168625 Byte)
step5.jpg (173659 Byte) step6.jpg (202041 Byte) step7-8.jpg (191468 Byte)
step9.jpg (215457 Byte)   click here to see the VRML model

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

Orbital Decay and micro-g levels Accumulated Momentum during Assembly TEA

Configuration Alternatives:

alternative1_step1_labeled.jpg (157450 Byte)
alternative1_step2.jpg (203691 Byte)
alternative1_variant1.jpg (179424 Byte)
Alternative 1 (Step 1) Alternative 1 (Step 2) Alternative 1a
alternative1_variant2.jpg (203779 Byte)
alternative2.jpg (192436 Byte)
alternative3.jpg (172820 Byte)
Alternative 1b Alternative 2 Alternative 3
alternative4.jpg (131283 Byte)
crew_quarter.jpg (154616 Byte)
crew_quarters.jpg (112223 Byte)
Alternative 4 Crew Quarters Alternative 1 Crew Quarters Alternative 2

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