The document provides an overview of a preliminary design review for a Mars flyby mission called Mars18. Key details include: - The mission would involve a two-person flyby of Mars launching in 2018 using existing commercial launch vehicles and capsules. - Four launch concepts were presented using Atlas V, Falcon Heavy, and Delta IV Heavy rockets with Dragon, Cygnus, or Centaur capsules. - Subsystem designs were outlined for structures, life support, radiation shielding, thermal control, attitude control, electrical power, communications, re-entry, and systems engineering. - Human factors considerations and methods for estimating economic costs were also summarized. The review identified remaining work to finalize the

1. Preliminary Design Review
- Mars18 -
The Mars Society International Student
Design Competition

2. Content
•
•
•
•
•
– Attitude and Orbit Control
System
– Electrical Power System
– Communications
– Re-entry and TPS
– Systems Engineering
Introduction
Launch Systems
Trajectory
Launch Concepts & TMI
Spacecraft Design
–
–
–
–
Structural Design
Life Support Systems
Radiation Shielding
Thermal Control System
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•
•
•
Human Factors
Economics
To be done
Support

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
IEEE Aerospace: Tito and Carrico, Feasibility Analysis for a
Manned Mars Free-Return Mission in 2018
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4. Introduction
• Competition backed by Dennis Tito and Mars Society in
cooperation with NASA Ames
• Pushing the envelope towards human Mars exploration
• Gaining public attention and generating public interest for
manned space missions
• Prepare students for future development
Schedule
Cost
projects with comparable goals
20%
30%
• Selection criteria
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. Schedule
• Critical Design Review: 14.02.2014
• Mars18 Deadline (Design Freeze): 28.02.2014
• Final Report: 14.03.2014
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7. 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.

8. Launch Concepts
Expensive
Conservative
Optimistic
Launcher
Less expensive
Payload
1 (Atlas HLV based)
Falcon 9
Atlas HLV
Atlas HLV
Dragon Rider
Cygnus & Tank
Centaur
3 (Atlas V551 based)
Atlas V 551
Atlas HLV
Delta IV Heavy
Dragon & Cygnus
Tank
Centaur
Launcher
Payload
2 (SpaceX based)
Falcon 9
Falcon Heavy
Falcon Heavy
Dragon Rider
Cygnus & Tank
Centaur
4 (Conservative)
Falcon 9
Delta IV Heavy
Atlas V 551
Delta IV Heavy
Dragon Rider
Cygnus & Tank
Tank
Centaur
8
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9. Launch Concepts
Concept
Cost Mio $
TRL Median
Date of first launch
1 (Atlas HLV based)
596,5
7,3
Sept. 2017
2 (SpaceX based)
416,5
7,2
Sept. 2017
690
8,3
Okt. 2017
586,5
8,8
Aug. 2017
3 (Atlas V551 based)
4 (Conservative)
Comparison:
Inspiration Mars Concept
Space Launch System &
Commercial Crew Launcher
Cost in Mio$ TRL Median
600-2100
6
Date of first launch
Dec. 2017
9
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10. Concept Atlas V551 (ULA)
Delta IV
Atlas V 551
(manned)
Atlas HLV
10
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11. Concept Atlas V551 (ULA)
11
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12. Concept Falcon Heavy (SpaceX)
Falcon 9
Falcon Heavy
Falcon Heavy
Payload:
Dragon Rider
Payload:
Cygnus &
Centaur
Payload:
Centaur
12
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13. Concept Falcon Heavy (SpaceX)
to Mars
Trans-Mars-Injection
(TMI)
Sept. 2017
Dez. 2017
Dez. 2017
04. Jan. 2018
13
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14. Trajectory
Start orbit
Start date
04.01.2018
Delta-V departure
Earth
4825 m/s
Arrival date
19.05.2019
Duration
1.37 years
V_inf arrival
Departure
350 x 350 km
8786 m/s
Velocity at 120 km 14143 m/s
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Capture
Flyby

15. Trajectory
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16. Structural Design
• Sufficient space, protection, simple and inexpensive
deployment, support of all required structures
Conservative Designs
Advanced Designs
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17. Structural Design
Conservative Design
+ Costs and risks
+ Availability
+ Proven Design
 Less spacious
 Radiation Protection
Modifications required
SpaceX - Dragon Rider
Orbital Science - Cygnus Adv.
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18. 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)
Empty Mass
Pressurized
Unpressurized
Power
Dragon Rider
ca. 2360 kg
10 m³
14 m³
1500 W
Cygnus
ca. 1630 kg
27 m³
-
3500 W
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19. 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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20. Dirty
Laundry
Waste
ECLSS – Eating and Waste
Eating simple!?!
Waste Compactor
Waste
Shielding tile
W
a
t
e
r
Water System
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21. 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

22. Flowchart ECLSS
SABATIER
VPCAR
waste
TANKS
TANKS
brine
SPWE
FOOD
feces
CREW
4BMS
leakage compensation
urine
ACS
leakage
atmosphere
TCCS
CHX
TCS
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23. Radiation Protection against GCR
•
•
•
•
•
•
Gradual increase in shielding through PMC-tiling
Personal active dosemeters for astronauts
PE-blankets while sleeping (2 g/cm²)
Wearing of PE-vests whenever possible (1 g/cm²)
Additional shielding of 3 g/cm² PE in both capsules
Filling of remaining carrying capacity with PE-sheets
Shielded Area of Dragon
Capsule [m²]
30
25
20
15
10
5
0
0
250
Time [days]
~ 10 g/cm² + 3 g/cm²
~ 48 g/cm²
Trunk
Dragon
Cygnus
Diverse materials
Polyethylen (PE)
~ 10 g/cm² + 3 g/cm²
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Trunk
~ 48 g/cm²
500

24. Radiation Protection against SPEs
SPE
(detected by sensors)
~ 48 g/cm² diverse materials
Alignment towards sun
Ø: 2 m
~ 9 g/cm² water/feces
Trunk
~ 2,4 g/cm² water (decreasing) + tiles (increasing)
Dragon
Cygnus
Trunk
• Water gets replaced by feces to maintain shielding against SPEs
• PMC-tiles, wet wipes and desinfectant wipes can be used to
reinforce shielding (fixation with duct tape)
• Amifostin is dispensed after SPE
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25. Thermal Control System
• Dissipative and external
heat sources
• Assembly in Earth orbit
– ca. 8900 W
• Passing Venus orbit
– ca. 6700 W
• Mars flyby
– ca. 4300 W
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26. Thermal Control System
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27. 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]
• Control Algorithm: ModelPredictive-Control (MPC)
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28. Attitude & Orbit Control System
• Rendezvous maneuver also by MPC
• Overall model to save propellant
28
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29. Electrical Power System
Goal: provide continuous average power and withstand daily
power peaks
• Sizing Case: Arrival at Mars after ca. 250 days
– Largest distance to Sun, moderate degradation
– Including environmental, array and system losses
– Shadow times during launch/docking and behind Mars
Average
Required Power
Power
3400 W
5750 W
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30. Electrical Power System
• UltraFlex arrays (GaAs) as primary power source
• Secondary storage: Regenerative fuel cells
– Rechargeable, covering daily power peaks, launch/docking
– Highly-integrated into ECLSS (no extra tanks)
Mass [kg]
Solar Arrays
182.6
Secondary Energy Storage
108.2
Power Distribution
70.9
Total Mass
361.7
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31. Electrical Power System
• Dimensions are to scale
2.0m
5.8m
10.2m
3.6m
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32. 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
32
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33. Antenna Systems
• Parabolic high gain antenna (min. 2.5 m)
– High data rate X-band transmission and reception (mainly
science data, pictures, videos)
– 4 channels with max. 250 kbps
– ITU conformable center frequencies (DL 8.45 GHz, UL 7.20 GHz)
– Low data rate S-band TT&C
• Low gain antennas
– Low data rate omni- directional S-band transmission and
reception for engineering data, commands, emergency
• Electra UHF system
– For Mars relay network communication during flyby
33
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34. 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
34
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35. Re-entry
• 3 passes through atmosphere
before re-entering
• Keep the load factors
within a limit of 5 g
• Lower heat flux peaks
Peak Load
< 4.5g
Duration
ca. 7h
Type
Ablative
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36. Re-entry
• Altitude and velocity during re-entry
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37. Thermal Protection System
• Use of PICA-X as in Dragon-C1
PICA -X
TRL
7
Density Max. Heat Flux Max Temp.
0.27 g/cm³ 1200W/cm²
>1920K
• Increase in thickness due to higher integral heat load
• PICA-X is 10-times cheaper then PICA, ready for 2018
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38. 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%
• Overall system margin of 20%
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39. Mass Budget
Mass [kg]
Structure
6%
25%
4 022
25%
Attitude and Orbit Control System
1 729
11%
733
5%
1 500
9%
800
5%
Radiation Protection
6%
2 032
13%
ECLSS
3 197
20%
Thermal Control System
913
6%
Health Care
877
6%
System Total
15 804
100%
System Total + Margin (20%)
18 964
Electrical Power System
Thermal Protection System
20%
Communication System
11%
13%
5%
5%
9%
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40. 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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41. Human Factors
Physical health
Mental health
•
•
•
•
Using medication and physical workouts to keep
up the blood circulation
Controlled diet plans with a certain amount of
iron and sodium chloride
Anticoagulants to influence the blood viscosity
and composition and prevent thrombosis
•
•
•
Biofeedback: the measurement of various
physical features that are unconscious
Distractions and entertainment
Individual configuration and layout of personal
space with participation of crew members.
Audio-visual-stimulation as a method to
enhance mental fitness
E-health
Training & food
•
•
•
•
Healthvest measures medical parameters
(e.g. ECG, blood pressure, temperature etc.)
Monitoring the vital parameters on earth and
prevent pathological changes
Frequent blood-gas analysis to examine the
astronauts on infections or radiation exposure
•
•
Physical training to maintain the blood
circulation and assist the muscle-vein-pump
Preventing osteoporosis and the decomposition
of bones and muscles
Ensure the physical fitness of the astronauts
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42. Technical devices
Healthvest
Brainwave stimulation
Monitoring device
Gym
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43. Economics - Cost estimating methods
• Parametric: mathematical equations relating cost to one or
more physical or performance variables associated with the
item being estimated
𝜷
𝑺𝒚𝒔𝒕𝒆𝒎 𝑪𝒐𝒔𝒕 = 𝜶 ∗ 𝑸 ∗ 𝑴
𝜩∗
𝜹 𝑺∗
𝟏
( 𝑰𝑶𝑪−𝟏𝟗𝟎𝟎))
𝜺
∗ 𝑩ф ∗ 𝜸 𝑫
(Advanced Missions Cost Model (AMCM)
• Build-up: historical data (e.g. detailed work hours and bills of
material)
• Analogy: the data is adjusted or extrapolated
43
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44. Comparison of estimated cost (build-up
and analogy) and cost of the AMCM
Estimated Cost
Structure
$427,500,000
Attitude and Orbit Control System
$822,400
Electrical Power System
$1,457,881
Propulsion Module
$900,000,000
Thermal Protection System
n/a
Communication System
$60,000,000
Radiation Protection
$3,004,550
ECLSS
n/a
Thermal Control System
n/a
Health Care
$27,900
Total
AMCM
$1,652,404,612
$1,998,184,167
$1,139,361,270
n/a
$1,159,495,114
n/a
$459,414,304
$7,540,528,352
n/a
$518,579,504
$1,397,812,731 $13,328,606,055
44
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45. To be done
•
•
•
•
•
Finish design, cost estimations
Risk management
Mission schedule, roadmap
Ground segment
Public outreach
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46. Unterstützung
•
•
•
•
•
•
Institut für Raumfahrtsysteme – Uni Stuttgart
ASTOS Solutions – Bahnbestimmung und -optimierung
Campus Konzept Stuttgart – Studentische Unternehmensberatung
Constellation – Studentische Nachwuchsforschungsgruppe
DGLR – Stuttgart
BrainLight GmbH – Marktführer für Entspannungstechnologie
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47. Unterstützung
Was wir benötigen:
• Reisekostenzuschüsse (Abschlusspräsentation in den USA)
• Professionelle Meinungen und Korrekturleser
• Finanzielle Unterstützung fürs Teambuilding (T-Shirts etc…)
Was für sie drin ist:
• Name und ggf. Logo im Abschlussbericht (wird veröffentlich)
• Chance sich vor motivierten Studenten zu präsentieren
• Kontakt zu Studenten in ihrem Fachgebiet
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48. Thank you for your attention!
Questions?
Kontakt:
D.Fries@Mars18.de
L.Teichmann@Mars18.de
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49. Media Sources
•
•
•
•
•
•
•
•
•
•
•
http://casolarco.com
http://s400.photobucket.com/user/Donaldyax/
Emil Nathanson, Vorlesung Raumfahrttechnik 1
Johnson, J., and Marten, A., “Testing of a High Efficiency High Output Plastic Melt Waste
Compactor”, AIAA-2013-3372, 2013.
http://www.coconutsciencelaboratory.com
www.nasa.gov
www.spacex.com
www.orbitalsciences.com
Star Trek
http://www.ulalaunch.com/site/pages/Products_AtlasV.shtml
www.planetaryresources.com
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50. ECLSS - Subsystems
o
Sabatier
Converts CO2 from 4BMS to H2O and CH4 using H2
o
4BMS - 4-Bed Molecular Sieve
Filters CO2 from atmosphere
o
TCCS - Trace Contaminant Control System
Filters gaseous and vapor contaminants, airborne particulates and microbes
o
CHX - Condensing Heat Exchanger
Cools atmosphere through condensation of atmospheric moisture (temperature and humidity control)
o
SPWE - Solid Polymer Water Electrolysis
Produces H2 and O2 from H20
o
VPCAR - Vapor Phase Catalytic Ammonia Removal
Produces clean H2O from waste water trough evaporation, condensation and other processes
o
ACS – Atmosphere Control System
Monitors and controls the operation of all subsystems
o
HEHO-PWMC – High Efficiency High Output Plastic Waste Melt Compactor
Melts trash to shielding tiles and removes water from trash
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