2. Content
– Attitude and Orbit Control
System
– Electrical Power System
– Communications
– Re-entry and TPS
– Systems Engineering
•
•
•
•
Introduction
Launch Systems
Trajectory
Launch Concepts &
Trajectory
• Spacecraft Design
–
–
–
–
Structural Design
Life Support Systems
Radiation Shielding
Thermal Control System
•
•
•
•
Human Factors
Economics
To be done
Supporters
3. Introduction
The Mars Society International Student Design Competition:
“Design a two-person Mars flyby mission for
2018 as cheaply, safely and simply as possible”
Phase 0/A/B Study
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4. Introduction
• Pushing the envelope towards human Mars exploration
• Gaining public attention and generating public interest for
manned space missions
• Prepare students for future development
projects with comparable goals
Schedule
Cost
• Selection criteria
20%
30%
Simplicity
20%
Technical
Quality
30%
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5. Team
• Over 40 students from aerospace engineering, economics,
medicine and others in the 1st to 9th semester
• Faculty advisors from the Institute of Space Systems
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6. Requirements
• Defined mission statement and top-level objectives
• Derived requirements on system and subsystem level
ID
TL.1
TL.2
TL.3
TL.4
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Description
The mission shall be executed by two astronauts.
The mission objective is to complete a mars flyby and safely
return to earth.
The mission will commence in the year 2018.
The mission shall result in scientific progress.
11. Spacecraft Design
– Attitude and Orbit Control
System
– Electrical Power System
– Communications
– Re-entry and TPS
– Systems Engineering
•
•
•
•
Introduction
Launch Systems
Trajectory
Launch Concepts &
Trajectory
• Spacecraft Design
–
–
–
–
Structural Design
Life Support Systems
Radiation Shielding
Thermal Control System
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•
•
•
•
Human Factors
Economics
To be done
Supporters
12. Structural Design
• Baseline: sufficient space, simple and inexpensive deployment,
support of all required structures
Conservative Designs
Advanced Designs
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13. Structural Design
Conservative Design
+ Costs and risks
+ Availability
+ Proven Design
Less spacious (but above tolerable
limit by NASA Standards)
Modifications required
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14. Structural Design
• Sizing structure for launch and re-entry loads
– Peak bending moment and compressive force
• Addition of supportive structure
– Secondary (e.g. International Standard Payload Racks)
– Docking adapters
• Utilizing proven materials (Aluminum, Titanium)
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15. ECLSS – Environment Control and Life
Support System
Recycling of most resources (almost closed system)
Urine
Water
Management
H2O
Air
Management
O2
Waste Water
CO2
Water
Management
Air
Management
Food
Feces
Storage
Hygiene Products
Storage
Waste
Clothes
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16. Open Loop <–> Closed Loop
Equivalent System Mass (ESM) [kg]
10000
9000
Closed System (VPCAR)
8000
Closed System (MF+VCD)
7000
Open System
6000
- 5500kg
5000
4000
- 1300kg
3000
2000
1000
0
100
200
300
Mission Duration [d]
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400
500
18. Radiation Protection against SPEs
SPE
(detected by sensors)
diverse materials
Alignment towards sun
Ø: 2 m
water/feces
water (decreasing) + tiles (increasing)
Trunk
Dragon
Cygnus
Trunk
• Water gets replaced by feces to maintain shielding against SPEs
• Amifostin is dispensed after SPE
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19. Thermal Control System
• Dissipative and external
heat sources
Critical Points:
• Assembly in Earth orbit
• Passing Venus orbit
• Mars flyby
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21. Attitude & Orbit Control System
• Control system consisting of
– Hydrazine thrusters [orbit]
– Momentum wheels [attitude]
– Resistojets [desaturation]
• Sensor system consisting of
– Sun sensors, star trackers
– Inertial measurement units
– GPS [Rendezvous]
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22. Electrical Power System
Goal: provide continuous average power and withstand daily
power peaks
• Sizing Case: Arrival at Mars after ca. 230 days
– Largest distance to Sun, moderate degradation
– Including environmental, array and system losses
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23. Electrical Power System
• Primary power source: UltraFlex arrays (4 x ∅5m)
• Secondary storage: Regenerative fuel cells
• Power management and distribution with 11.4 kW/kg
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25. Communications
• Goals
– Providing failure-safe communication between the spacecraft
and ground stations on earth
• Limitations
Antenna size/fairing space
Suitable ground stations limit frequency bands selection
Power consumption
• Environment
– Interference from solar radiation
– Communication blackout during flyby
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26. Phases of communication
Near Earth phase
– Live streaming
– Engineering data
Cruise phase
– Pictures, videos
– Science data
– Engineering data
Relay communication phase
– Science and engineering data,
emergency link
Cruise phase
– Pictures, videos
– Science & Engineering data
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27. Re-entry
• 3 passes through atmosphere
before re-entering
• Keep the load factors
within a limit of 5 g
• Lower heat flux peaks
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28. Thermal Protection System
• Use of PICA-X as in Dragon-C1
• Increase in thickness due to higher integral heat load
• PICA-X is 10-times cheaper then PICA
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29. Systems Engineering
• Mass, volume and power budgets
– Pressurized, unpressurized and packed volume
– Average, peak and waste power
• Element margins depending on technology readiness level
and amount of required modifications
– 5%, 10% and 20%
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30. Spacecraft Design
– Attitude and Orbit Control
System
– Electrical Power System
– Communications
– Re-entry and TPS
– Systems Engineering
•
•
•
•
Introduction
Launch Systems
Trajectory
Launch Concepts &
Trajectory
• Spacecraft Design
–
–
–
–
Structural Design
Life Support Systems
Radiation Shielding
Thermal Control System
•
•
•
•
Human Factors
Economics
To be done
Supporters
30/ 37
31. Human Factors
2 Ensure physical health
To ensure physical health during the
whole trip the team has to be prepared
for all medical risks. Therefore the team
supplies
medical
treatment
and
prevention .
3 e-Health
Offering solutions for a 24/7
monitoring and documentation of
all medical parameters through an
health vest. The e-Health system
offers self-treatment options.
1 Preselecting & Preparation
The Team sets up the right criteria for
the Preselection (age, experience,
health situation, profession, ..).
Moreover the astronauts have to be
prepared mentally and physically.
4
Training & Food
To prevent muscle degradation due to
microgravity we provide training
equipment and a suitable nutritional
protocol.
5 Ensure mental health
To establish and keep the astronauts
mentally fit during the whole trip is a
necessary key for a successful mission.
This can be ensured by using audiovisual stimulation, a motivation and
entertainment kit.
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32. Economics - Cost estimating methods
• Parametric: mathematical equations relating cost to one or
more physical or performance variables associated with the
item being estimated
• Build-up: historical data (e.g. detailed work hours and bills of
material)
• Analogy: the data is adjusted or extrapolated
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33. To be done
•
•
•
•
•
•
Finish design, cost estimations
Risk management
Mission schedule & development roadmap
Ground segment
Science
Public outreach
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35. Unterstützung
Was für sie drin ist:
• Name und Logo im Abschlussbericht/Präsentation
• Mediale Präsenz (z.B. Stuttgarter Nachrichten, Radio, etc.)
• Chance sich vor motivierten Studenten zu präsentieren
• Image bestärken als innovatives und zukunftsgestaltendes
Raumfahrtunternehmen
Was wir benötigen:
• Professionelle Meinung und Korrekturleser
• Finanzielle Unterstützung fürs Teambuilding (T-Shirts, etc.)
• Reisekostenzuschüsse (Abschlusspräsentation in den USA)
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