Mark Baker Mario Botros Terry Huang Erin Mastenbrook Paul Schattenberg

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