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Team Ptolemy. Mark Baker Mario Botros Terry Huang Erin Mastenbrook Paul Schattenberg David Wallace Lisa Warren. Outline. Introduction Mission Statement Concept of Operations Trade Trees / Specifications Structures Living Units Launch Vehicle - PowerPoint PPT Presentation
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Mark BakerMario BotrosTerry HuangErin MastenbrookPaul SchattenbergDavid WallaceLisa Warren
Team Ptolemy
Outline
IntroductionMission Statement
Concept of OperationsTrade Trees / Specifications
StructuresLiving UnitsLaunch VehiclePropulsionPowerControlsCommunicationsLife Support
AdvantagesQuestions
Introduction
Mission Statement:Our mission is to expand the domain of humanity beyond the Earth for the betterment, preservation, and advancement of all humankind by creating a mobile habitat capable of long-duration, exploratory voyages while ensuring the physical and psychological well-being of its inhabitants.
Concept of Operation
Launch individual components into
GEO
Assemble components
autonomously in GEO
Send crew to assembled vehicle
Transfer from GEO to Earth-Moon L1
Transfer from Earth-Moon L1 to Earth-
Sun L1
Transfer from Earth-Sun L1 to near earth asteroid
Leave near earth asteroid and enter
LEO
Return crew to Earth via capsule
Ptolemy
12m10m
6m
50m
5m
Estimated Total Weight: 300MT
16m
z
xy
Living podsConnecting arm
Main hub
Power generationMain propulsion system
Communications
z
xy
• Truss design for strength efficiency• Inner pressurized tube for crew
mobility• 50 m length, 3 m outer diameter
Connecting Arm
𝐹 (𝑥 )=𝜔2(𝑟 +𝑥)[ (𝐿−𝑥 )𝑚𝑇+𝑚𝑐] (kg/m)
𝑚𝑐=𝑚𝑎𝑠𝑠𝑜𝑓 𝑐𝑎𝑝𝑠𝑢𝑙𝑒(𝑘𝑔)
Artificial Gravity Calculations
𝑎𝑐=𝑟 𝜔2
Living Units
• Occupancy: 6 crew members
• Volume/Weight: 330 m3/20MT
• Radiation Protection: Greater than International Space Station
• Ballistic Protection: Micrometeorite and Orbital Debris Shield
BA - 330
• Occupancy: 16 crew members
• Volume/Weight: 2100 m3/65MT
• Radiation Protection: Greater than International Space Station
• Ballistic Protection: Micrometeorite and Orbital Debris Shield
BA - 2100
Launch Vehicle
Launch Vehicle
Atlas V-551 Delta IV Heavy
Falcon 9 Heavy SLS 130 MT
Propulsion
Propulsion
Low Thrust
Solar Sails Ion Thruster
High Thrust
Solid Rocket
Bipropellant Rocket
Propulsion System
• DC Power Required : 200 kW
• Thrust: 5.7 N
• Exhaust speed: 50 km/s
• Specific Impulse: 5000 s
• Thruster efficiency: 72%
Vasimr VX-200 ComparisonIon Thruster
Effective Exhaust Velocity: 50 km/s
Specific Impulse: 5,000 s
Fuel Mass: 620 kg
Bipropellant Rocket
Effective Exhaust Velocity: 5 km/s
Specific Impulse:500 s
Fuel Mass:8,200 kg
Power
Power
Solar Cells
Copper Indium Gallium Selenide
Gallium Arsenide
MultijunctionDye-sensitized
Cells
Fuel Cells Nuclear
Fast Nuclear Reactor
Thermal Reactor
Power Specifications
Solar Cells• Gallium Arsenide Multijunction Cells
• Clean and renewable energy
• Typical efficiency of 30%
• Most efficient type of solar cell
• Stored in Lithium – Ion batteries
Nuclear Reactor• TRIGA Mark III
• Power output up to 1 MW
• Pulses up to 6 MW
• Fuel – High or low enriched uranium
• Negative thermal coefficient
Controls
Attitude Determination &
Control
Sensors
GPS
IMU
Star Tracker
Sun Sensor
Magnetometer
Actuators
Reaction Jets
Reaction Wheels
CMGs
Solar Sails
Controls Specifications
Sensors• GPS – determine position near Earth
• IMU – measure attitude, velocity, and acceleration
• Star Tracker – determine position outside of GPS range
• Sun Sensor – change angle of solar cells.
Actuators• Reaction Jets
• Controls Attitude
• Controls Nutation
• Controls Spin Rate
• Station Keeping
• Rendezvous Maneuvering
Communication systems
External• Uplink and downlink radios with high
data transfer rate
• Backup systems with low transfer rates for redundancy
• Satellite with maneuverability to maintain contact with Earth-Based ground systems
Internal• Internal Audio Subsystems provides
intercom, telephone and alarm systems
• Two-way audio and video communications among crew
Life Support
Food
Farming
Hydroponics Clay Particles Peat-Moss
Storing
Refrigerated Food Frozen Food Thermostabilized Food
Life Support Systems
Elektron: Electrolysis splitting water
molecules into oxygen and hydrogen
Vika: Burning of solid lithium perchlorate to
create oxygen
Vozdukh: Uses regenerable
absorbers to remove carbon dioxide from
the air
Life Support Specifications
• Stored at room temperature
• Fruits and fish thermostabilized in easy to open cans
• Entrees in flexible pouches are heated and cut open
• Dehydrated drinks to be mixed with water or fruit juice
Thermostabilized Food
Weight of Food per Crew per Day (kg)
# Crew Members # Days Estimated Total
Food Weight (kg)Total Planned Food
Weight (kg)Total Planned Food
Storage Surface Area (m²)
0.58 12 730 5080.8 7621.2 43.07
Food Area Calculations Estimated Volume of 1 Meal (in³) 200
# Meals per Day 3 # Days 730 # Crew 12
Total Food Volume (in³) 5,256,000 Total Food Volume (m³) 86.13
Surface Area Required if stacked 3 meters high (m²) 28.71
Total Agricultural Surface Area needed (m²) 672
Advantages
• Food• Reduction in volume and surface area• No refrigeration or freezing system needed
• Solar cells• Renewable energy• Little maintenance required
• Nuclear power• Lowest cost to power ratio• Independent of environment
• Structure• Using existing model for the living units (Bigelow Aerospace Models)
Questions?
Backup Slides
• Radiation exposure causes direct damage to DNA and indirect effects on health due to generation of reactive oxygen species.
• Total area to be shielded: 1460 m2
Material Surface area density
Mass required
Aluminum 55g/cm2 802500 kg
Polyethylene 20g/cm2 291830 kg
Radiation Shielding
Approximate Days Required to Achieve Required ΔV
Number of Engines
GEOEML1 EML1C3=0 C3=0NEO Asteroid
1 507 days 51.1 days 294.0 days
2 254 days 25.6 days 147.1 days
3 169 days 17.0 days 98.1 days
Required ΔV
mT: mass of arm mC: mass of capsule
L
ω
r
Connecting Arm Calculations
Launch Vehicle Specifications• Atlas V-551
– Payload to LEO: 18,814 kg– Payload to GTO: 8,900 kg
• Delta IV– Payload to LEO: 22,560 kg– Payload to GTO: 12,980 kg
• Falcon 9– Payload to LEO: 53,000 kg– Payload to GTO: 12,000 kg
• Space Launch System– Payload to LEO: 130,000 kg– Payload to GTO: no data