Inspiration Mars International Student Design Competition

Mars Society 2014 International Conference

League City, TX

Keio University Purdue University

2

Orion

Design Philosophy Critical factors (from QFD):

Development time (TRL)

Crew safety (reliability)

Cost (mass)

Kibo

Cygnus

3

Candidate

Modules

Mission Overview

Crew 2

Duration 501 days

Mass 35 metric tonnes (mT)

Volume

(open)

70 m3 (~ space shuttle cabin)

Cost $ 4.4 Billion

23 m

4

Concept of Operations

5

Trajectory & Launch

6

Trajectory & Launch

Hab. MPLM

15.6 mT

ERV Dragon

4.2 mT

PMA 1.1 mT

SM ATV mod.

16.8 mT

PM - DCSS

Required IMLEO: 126 mT

5-m

30.7 mT

5-m

30.7 mT

5-m

30.7 mT

7

Launch Architecture

Image: SpaceX

Falcon Heavy 53 mT to LEO

Image: NASA

SLS 70 mT

8

1st Launch Opportunity

Nov. 25 – Dec. 9 DCSS 5 m

30.7 mT

4.87 mT margin

ATV

16.8 mT

Baseline:

Launch Architecture

Image: SpaceX

Falcon Heavy 53 mT to LEO

Image: NASA

SLS 70 mT

9

1st Launch Opportunity

Nov. 25 – Dec. 9 DCSS 5 m

30.7 mT

4.87 mT margin

ATV

16.8 mT

2nd Launch Opportunity

Dec. 9 – Dec. 23 DCSS 5 m

30.7 mT

8.39 mT margin

Habitat

11.8 mT

PMA

1.1 mT

Baseline:

Launch Architecture

Image: SpaceX

Falcon Heavy 53 mT to LEO

Image: NASA

SLS 70 mT

10

1st Launch Opportunity

Nov. 25 – Dec. 9 DCSS 5 m

30.7 mT

4.87 mT margin

ATV

16.8 mT

2nd Launch Opportunity

Dec. 9 – Dec. 23 DCSS 5 m

30.7 mT

8.39 mT margin

Habitat

11.8 mT

PMA

1.1 mT

3rd Launch Opportunity

Dec. 23 –Jan. 2 DCSS 5 m

30.7 mT

17.10 mT margin

ERV

4.2 mT

Baseline:

Distance from Earth (AU)

0.0 0.5 1.0

TMI

Jan. 4, 2018

Mars

Alt. 240 km

Aug. 20, 2018

Return

May 20, 2019

Image: Eliasen Aerospace

Visualization Laboratory

Interplanetary Trajectory

11

Distance from Earth (AU)

0.0 0.5 1.0

TMI

Jan. 4, 2018

Mars

Alt. 240 km

Aug. 20, 2018

Return

May 20, 2019

Image: Eliasen Aerospace

Visualization Laboratory

Interplanetary Trajectory

Earth Departure

Image: Eliasen Aerospace

Visualization Laboratory

200-km LEO

1st ellipse:

1.073 km/s

2.49 hours

2nd ellipse:

1.486 km/s

12.99 hours

TMI / escape:

2.305 km/s

Excess: 0.123 km/s

12

Distance from Earth (AU)

0.0 0.5 1.0

TMI

Jan. 4, 2018

Mars

Alt. 240 km

Aug. 20, 2018

Return

May 20, 2019

Image: Eliasen Aerospace

Visualization Laboratory

Interplanetary Trajectory

13

Earth Return

Aerocapture

Image: Eliasen Aerospace

Visualization Laboratory

15.9 hrs

Altitude: 73 km

Re-entry vel.: 14.2 km/s

Effective ΔV: 3.7 km/s

Capture vel.: 10.5 km/s

Optimized Aerocapture

Parameter

Ballistic

Re-entry

Lifting

Re-entry

Altitude (km) 70 73

Peak heat rate (W/cm2) 2400 1700

Max g load (Earth gs) 7 5

Total heat load (kJ/cm2) 125 127

Image: SpaceX

14

Vehicle Sub-systems

15

ECLSS

Photos courtesy of NASA

Carbon Dioxide

Removal Assembly

Oxygen Generation

Assembly

Sabatier System

CO2

CO2

O2

H2O

Urine Processor

Assembly

Water Processor

Assembly

H2O

H2O

(waste water)

H2O (gray water)

H2O (urine)

H2O

O2

LiOH Canister

O2

CO2

H2O

x 143 days

x 143 days

x 143 days

Simulated using SICLE Space Systems Development Corporation

16

Vehicle System: ADCS Nominal Interplanetary Turn Rate ERV

16 Dracos

NTO/MMH

Sensor suite

3 star trackers

12 sun sensors

3 IMUs

Control system

28 Resistojets

ECLSS waste

4 reaction wheels

17

Vehicles System: EPS/TCS

Mars Encounter

700 W/m2

Perihelion

2500 W/m2

Design driven by insolation level

18

Vehicles System: EPS/TCS

ATV produces 4.9 kW at Earth

production capacity must be increased by ~350%

9.2 kW

5.5 kW

19

Vehicles System: EPS/TCS

Batteries:

X4 Li-ion

28 DCV

130 kW•hr

1 ton total

Higher Energy Density

ATK UltraFlex Panels:

x4, 65 m2 total

12 kW min at EOL

ISS Heritage Radiators:

x2, 15 m2 total

Reject 50 kW at 160 °C

~14 hours of normal operations

~24 hours of emergency operations

20

Vehicles System: EPS/TCS

700 W/m2

Mars Encounter

700 W/m2

2500 W/m2

Perihelion

Passive Thermal Control

21

COMMS / C&DH

DSN Usage: 24 hours for TT&C

Estimated Cost: $138

million

Onboard computer 3 on ATV and 3 pairs on

Dragon

RAD5500 Processors

Power requirements 0.1 W for 3 solid state

recorders

LEO

Service: NASA TDRSS

Uplink: Ka Band

Downlink: Ka Band

CRUISE

Service: DSN

Uplink: Ka Band

Downlink: Ka Band

MARS FLYBY

Service: DSN & MRO/MAVEN relay

Uplink: Ka Band

Downlink: X band / Ka Band

Mars Orbiter

22

Human Factors

23

Galactic Cosmic Rays

(Isotropic, Continuous)

Solar Proton Events (Directional, Discrete)

Radiation Exposure

Van Allen Belts (During TMI and EDL Only)

Sources of ionizing radiation, modeled via NASA OLTARIS program:

Rapp, 2006

Assume:

- Only shielding from spacecraft pressure hull, average of 5 g/cm2 of Aluminum

- A single large flare (baseline October, 1989) with crew sheltering in Dragon,

using the entire spacecraft (60 g/cm2) as a shield.

518 mSv GCR + 40 mSv VAB + 144 mSv SPE

+ 300 mSv Previous Flights

24

Crew Selection and Training

Andy Thomas (62) and Shannon Walker (48)

Image: NASA

Crew Selection Age

Astronaut status

Physical intimacy

Marital status

Child factor

Image: NASA

Training Medical

Operations

Maintenance

Science payloads

25

Image: NASA

“If you can, make it feel like home” - Eugene Cernan

Human Factors - Psychology

Potential Stresses: Privacy, Isolation, Monotony, Conflict

26

“If you can, make it feel like home” - Eugene Cernan

Human Factors - Psychology

Potential Stresses: Privacy, Isolation, Monotony, Conflict

Mitigation Strategies: Best Practices: ISS, MDRS, Skylab, MIR

Spacecraft interior (Schlacht & Birke, 2010)

Natural elements (Bates & Marquit, 2010)

Personal Activities (Ono & Schlacht, 2010)

Space wear

Cultivation

(Living Farm)

Indirect Lighting

27

Payload

Observatory

• Scientific Observations

• Mental Occupation

Image: CNET

Image: NASA

Image: NASA

Protein Crystal Growth Experiment

• Lack of convection + precipitation

• Develop higher quality pharmaceuticals

Image: Made in Space

3D Printing • Use for generation of spare parts/tools

• Allows for creative experimentation

Radiation and General Health Monitoring • Area Passive Dosimeter for Life-Science Experiments

in Space (PADLES)

• Position Sensitive Tissue Equivalent Proportional

Chamber (PS-TEPC)

Image: KEK

28

Daily schedule

Note: for variety, schedules will be modified throughout flight

6:00 am Wake up,

breakfast

7:30 am Video log,

medical

inspection

8:15 am Housekeeping

9:00 am Exercise

Maintenance

11:00 am Maintenance

Exercise

1:00 pm Lunch

2:00 pm Private time

2:30 pm Research

experiments

4:15 pm Hobby

Housekeeping

5:15 pm Housekeeping

Hobby

6:15 pm Video log,

medical

inspection

7:30 pm Dinner

8:30 pm Entertainment,

relaxation,

private time

9:30 pm Sleep

Key: Crew 1

Crew 2

Both

Logistics & Development

30

Risk Management

Measures of Success

1. Crewed Flyby of Mars

2. Crew Health and Well-Being

31

Risk Management

Risk Item Mitigation Strategy

7 Failure to meet target conditions upon

re-entry can jeopardize crew safety

Perform intensive ground simulations

and testing + fly aerocapture

demonstration mission(s)

46, 47 Degraded mental/physical health can

cause impaired judgment, depression,

diseases and loss of life

Implement rigorous testing prior to

crew selection, allow personal items,

incorporate exercise regime and

medical testing into daily routine

Low

Medium

High

Lik

elih

oo

d

Consequence

32

Risk Management

Risk Item Mitigation Strategy

7 Failure to meet target conditions upon

re-entry can jeopardize crew safety

Perform intensive ground simulations

and testing + fly aerocapture

demonstration mission(s)

46, 47 Degraded mental/physical health can

cause impaired judgment, depression,

diseases and loss of life

Implement rigorous testing prior to

crew selection, allow personal items,

incorporate exercise regime and

medical testing into daily routine

Low

Medium

High

Lik

elih

oo

d

Consequence

33

Risk Assessment

Junction Key

AND Gate

OR Gate Failure to safely re-enter

ERV

separation

Heat shield

failure

LOSS OF CREW

Aerocapture Re-entry

99% 97% 97%

94%

93%

34

Risk Assessment

Junction Key

AND Gate

OR Gate Failure to safely re-enter

ERV

separation

Heat shield

failure

LOSS OF CREW

Aerocapture Re-entry

99% 97% 97%

94%

93%

Note: Mission failure, not crew loss 35

Cost Summary

Project Management

Systems Engineering

Safety & Assurance

Spacecraft

Systems Integration and Test

Mission Operations

Launch Services

Ground Systems

Communications 36

($M)

Cost Summary

37

Development Schedule

Q3 Q4 Q2 Q1 Q4 Q3 Q3 Q1 Q2 Q1 Q4 Q2 Q4 Q3 Q1 Q3 Q2 Q4 Q1 Q2

Design Acquisitions & Modification Integration & Test Cruise

2014

Q3

2015 2016 2017 2018 2019

Cruise Post

38

Kanau 2018 Features

5G, LOW HEAT ENTRY

FLIGHT HERITAGE

HARDWARE

STAGED TMI /

ABORT OPTIONS ECLSS w/

SURPLUS

SPACEOUS +

COMFORTABLE HABITAT

ADAPTIVE EPS/TCS

39

Prospects for 2021

Image:

ULA

ACES propulsion module

Bioregenerative ECLSS

Image: CSS-Dynamac

Image: Bigelow Aerospace

Inflatable habitats

Image: NASA

Venus encounter Image: NASA

SLS

Image: MSRO

Artificial Gravity

40

This is our team…

This is our KANAU… 41

Questions?

5G, LOW HEAT ENTRY

FLIGHT HERITAGE

HARDWARE

STAGED TMI /

ABORT OPTIONS ECLSS w/

SURPLUS

SPACEOUS +

COMFORTABLE HABITAT

ADAPTIVE EPS/TCS

42

Questions?

43