mark baker mario botros terry huang erin mastenbrook paul schattenberg david wallace lisa warren...

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