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Preliminary Design Review - Mars18 -
The Mars Society International Student Design Competition
Content
• Introduction
• Launch Systems
• Trajectory
• Launch Concepts & Trajectory
• Spacecraft Design
– Structural Design
– Life Support Systems
– Radiation Shielding
– Thermal Control System
– Attitude and Orbit Control System
– Electrical Power System
– Communications
– Re-entry and TPS
– Systems Engineering
• Human Factors
• Economics
• To be done
• Supporters
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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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
• Selection criteria
Cost 30%
Technical Quality
30%
Simplicity 20%
Schedule 20%
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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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• Defined mission statement and top-level objectives
• Derived requirements on system and subsystem level
Requirements
ID Description
TL.1 The mission shall be executed by two astronauts.
TL.2
The mission objective is to complete a mars flyby and safely return to earth.
TL.3 The mission will commence in the year 2018.
TL.4 The mission shall result in scientific progress.
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Schedule
• Critical Design Review: 14.02.2014
• Mars18 Deadline (Design Freeze): 28.02.2014
• Final Report: 14.03.2014
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Launch Concepts
Concept Cost Mio $ Date of first launch
1 (Atlas HLV based) 596,5 Sept. 2017
2 (SpaceX based) 416,5 Sept. 2017
3 (Atlas V551 based) 690 Nov. 2017
4 (Conservative) 586,5 Aug. 2017
Inspiration Mars Concept Cost in Mio$ Date of first launch
Space Launch System & Commercial Crew Launcher
600-2100 Dec. 2017
Comparison:
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Concept 2 (SpaceX based)
to Mars
Sept. 2017 Dez. 2017 Dez. 2017 04. Jan. 2018
Trans-Mars-Injection (TMI)
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Trajectory
Departure
Flyby Capture
Start orbit 350 x 350 km
Start date 04.01.2018
Arrival date 19.05.2019
Duration 1.37 years
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Spacecraft Design
• Introduction
• Launch Systems
• Trajectory
• Launch Concepts & Trajectory
• Spacecraft Design
– Structural Design
– Life Support Systems
– Radiation Shielding
– Thermal Control System
– Attitude and Orbit Control System
– Electrical Power System
– Communications
– Re-entry and TPS
– Systems Engineering
• Human Factors
• Economics
• To be done
• Supporters
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Advanced Designs Conservative Designs
• Baseline: sufficient space, simple and inexpensive deployment, support of all required structures
Structural Design
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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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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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ECLSS – Environment Control and Life Support System
Food
CO2
H2O
Hygiene Products
Waste
Feces
O2
Water Management
Air Management
Water Management
Clothes
Storage
Air Management
Storage
Urine
Waste Water
Recycling of most resources (almost closed system)
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Open Loop <–> Closed Loop
0
1000
2000
3000
4000
5000
6000
7000
8000
9000
10000
100 200 300 400 500
Equ
ival
en
t Sy
ste
m M
ass
(ESM
) [k
g]
Mission Duration [d]
Closed System (VPCAR)
Closed System (MF+VCD)
Open System
- 1300kg
- 5500kg
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ECLSS – Eating and Waste
Eating simple!?! Waste Compactor
Waste
Shielding tile W
a
t
e
r
Water System
Dirty Laundry Waste
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Radiation Protection against SPEs
• Water gets replaced by feces to maintain shielding against SPEs
• Amifostin is dispensed after SPE
Dragon Cygnus Trunk Trunk
diverse materials
Ø: 2 m
water/feces
SPE (detected by sensors) Alignment towards sun
water (decreasing) + tiles (increasing)
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Thermal Control System
• Dissipative and external heat sources
Critical Points:
• Assembly in Earth orbit
• Passing Venus orbit
• Mars flyby
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Thermal Control System
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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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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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• Primary power source: UltraFlex arrays (4 x ∅5m)
• Secondary storage: Regenerative fuel cells
• Power management and distribution with 11.4 kW/kg
Electrical Power System
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Electrical Power System
10.2m
“Off the shelf”
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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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Phases of communication
Cruise phase
– Pictures, videos
– Science & Engineering data
Relay communication phase
– Science and engineering data, emergency link
Cruise phase
– Pictures, videos
– Science data
– Engineering data
Near Earth phase – Live streaming – Engineering data
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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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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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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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Spacecraft Design
• Introduction
• Launch Systems
• Trajectory
• Launch Concepts & Trajectory
• Spacecraft Design
– Structural Design
– Life Support Systems
– Radiation Shielding
– Thermal Control System
– Attitude and Orbit Control System
– Electrical Power System
– Communications
– Re-entry and TPS
– Systems Engineering
• Human Factors
• Economics
• To be done
• Supporters
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Human Factors
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.
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 .
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
2
3
Training & Food To prevent muscle degradation due to microgravity we provide training equipment and a suitable nutritional protocol.
4
Ensure mental health 5 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 audio-visual stimulation, a motivation and entertainment kit.
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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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To be done
• Finish design, cost estimations
• Risk management
• Mission schedule & development roadmap
• Ground segment
• Science
• Public outreach
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Supporters
• 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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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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Danke für Ihre Aufmerksamkeit!
www.mars18.de
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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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