mark baker mario botros terry huang erin mastenbrook paul schattenberg david wallace lisa warren...
TRANSCRIPT
Mark Baker
Mario Botros
Terry Huang
Erin Mastenbrook
Paul Schattenberg
David Wallace
Lisa 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
Multijunction
Dye-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