AAE 450: Laurel Brown, Project Manager; Eric Briggs, Assistant Project Manager1 AAE 450 Senior Design Formal Presentation aae450

AAE 450: Laurel Brown, Project Manager; Eric Briggs, Assistant Project Manager

1

AAE 450 Senior DesignFormal Presentation

http://roger.ecn.purdue.edu/~aae450

AAE 450: Project Management: Laurel Brown, Eric Briggs

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Mission Parameters

Routine transport Minimize propellant Achieve 99% reliability Replace 10% of cycler

mass every 2 1/7 years

Assumptions:Established system

Colony on MarsMartian water plentiful

04/18/23 AAE 450: Project Management: Laurel Brown, Eric Briggs

3

The Team

Project Management:Laurel Brown (PM)Eric Briggs (APM)

Aerodynamics:Ravi Mathur (GL)James Watson

Matt Adkins

Thermal Control:Brandon Owens (GL)

Eric Briggs (APM)Chris DennisKevin Miller

Dynamics & Control:Rebbecca Kacvinksy (GL)

Brenda EichelJimmy HidayatAaron Murphy

Gina PieriAmber Rist

Communications:Valerie Kost (GL)

Samantha MartinezAndrew Myer

Structures:Vicki Hoyle (GL)Jason Gromski

David PageJonah Skoog

Power:Daniel Chakraborty (GL)

Alex BohnertCristina GordonYen Ching Yu

Human Factors:Wes Dafler (GL)

Robin PinsonJames PinyerdMike Sufana

Propulsion:John Gedmark (GL)

Mark KuipersSee-Chen LeeGeoffrey OsierJoe Sherrick

Emily Vaughan


4

In the Year 2035…

Taxi (2)

Cargo vehicle (4/synodic period)

Tanker (4)

Cycler (4)

Vehicle Images: Jonah Skoog

Planets not to scale


5

Example of Ballistic Cycler Orbit

E4

M5

Orbit period : 4 2/7 yrs or 2 synodic periods

Time to repeat inertially: 30 yrs

Sun


6

Following Our Crew on Their Journey


7AAE 450 - 1/ 17/ 03, Project Manager, Section I Presentations, Laurel Brown 2

Taxi and Cargo at Launch

1

Nuclear Thermal Rockets - 6 Liquid Engines - 2

Nuclear Thermal Rockets - 4 Liquid Engines - 1

AAE 450 – 4/22/03, Propulsion Group

Geoffrey Osier: J. Gedmark, M. Kuipers, S. Lee, J. Sherrick, E. Vaughan


8AAE 450 - 1/17/ 03, Project Manager, Section I Presentations, Laurel Brown 2

Engines

Fuel – LOX/LH2

Thrust = 2,072,000 N

Burn time = 42 s

99.95% Reliable, never failed in launch

Fuel – LH2

Thrust = 893,400 N

Burn time = 355 s

Nuclear Thermal Rocket

2

Credit: Boeing / Rocketdyne

SSME




9AAE 450 - 1/ 17/ 03, Project Manager, Section I Presentations, Laurel Brown 2

Abort System

Escape 4 Solid Rocket Motors Thrust = 244,000

N/motor G Forces = 3.7 - 4

Landing Thrust = 148,000 N Parachutes can handle

landing Complete System Weight

2215 kg

3



AAE 450: Structures: David Page, Vicki Hoyle, Jonah Skoog, Jason Gromski

10

Taxi Vehicle

14m

23.3m

Crew Capsule

Engines and Propellant

Component Mass (kg)

Vehicle Systems 13,280

Heat Shield 10,580

Support Structure 16,290

Engines 25,070

Inert Mass 65,220

Payload Mass 6,630

Propellant Mass 112,000

Liftoff Mass 183850

AAE 450: Structures: David Page, Vicki Hoyle, Jonah Skoog, Jason Gromski

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Cargo Vehicle

Engines and propellant

Docking port

Cargo payload

Water

20 m

3 m

0.8 m

10.6 m

Component Mass (kg)

Vehicle Systems 7,640

Support Structure 32,110

Engines 25,070

Inert Mass 64,820

Payload Mass 79,300

Propellant Mass 188,000

Liftoff Mass 332,120

14 m

31.7 m

AAE 450: Dynamics & Controls: Gina Pieri, B. Eichel, J. Hidayat, R. Kacvinsky, A. Murphy, A. Rist

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Rendezvous in LEO

Courtesy of: Jonah Skoog

Taxi + Cargo

Courtesy

of: Jonah Sko

og

Tanker

Step 1: Cargo vehicle launches Step 2: Taxi launches and docks with cargo Step 3: Taxi-cargo system docks with tanker


13

Courtesy

of: Jonah Sko

og

The Tanker System

Tanker reduces total propellant by 36%

Fact: less propellant required to launch off Mars than off Earth

Assumption: water available on Mars


14

More Dynamics and Control Issues

Hardware selection

Disturbance torques

Model vehicle motion

Attitude control

Courtesy of: B

oo-Ki S

cientific Co.

AAE 450: Human Factors: James Pinyerd, Wes Dafler, Robin Pinson,Mike Sufana

15

Taxi Flight Deck

“Work Area” Vital components Control Center

for the Taxi

Multi-Purpose Collapsible chairs Exercise equipment

ARR

Power

Water

Flight Controls

AAE 450: Human Factors: James Pinyerd, Wes Dafler, Robin Pinson,Mike Sufana

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Taxi Mid-Deck

“Living Quarters” Personal/Hygiene Social atmosphere

Airlock Ability to fix problems Sense of safety for crew

Health WCS

Wardroom

Airlock

AAE 450: Communications: Andrew Myer, Valerie Kost, Samantha Martinez

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Communications Links

Deep Space Network (DSN)

11-meter34-meter

Cargo

Taxi

Tanker

Cycler

Ka-Band

Ka-Band

S-Band

S-Ba

nd

X-Ban

d

S-Band


Canberra Complex, Australia

http://deepspace.jpl.nasa.gov/dsn/gallery/canberra4.html


18

Secondary and Support Vehicle Communications

11-meter34-meter


Cargo

Taxi

Tanker

Ka-Band

S-Band

X-Band

S-Band

http://eo1.gsfc.nasa.gov/Technology/xpaa.htm

http://www.allentele.com/newsrm/prodnews/iwce0222898.html

AAE 450: Dynamics & Control: Brenda Eichel, J. Hidayat, R. Kacvinsky, A. Murphy, G. Pieri, A. Rist

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Rendezvous of Taxi with Cycler

Injection of taxi-cargo vehicle onto hyperbolic transfer orbit

Rendezvous in 1.3 days

Abort options

*Vehicle illustrations courtesy of Jonah Skoog

AAE 450: Dynamics & Control: Brenda Eichel, J. Hidayat, R. Kacvinsky, A. Murphy, G. Pieri, A. Rist

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Docking Maneuvers

*Illustrations courtesy of Jonah Skoog


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Break #1

BREAK #1

04/18/23 AAE 450: Structures: Jonah Skoog, Vicki Hoyle, David Page, Jason Gromski

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Cycler System Layout

Nuclear Reactor

Small Hab. Module

Comm Dish Solar Panels

Ion Thruster

LargeHab.Module

Radiators

Docking Hub

Passage TubePassage

Truss

De-spin Thruster

Junction Node

Docking Passage

AAE 450: Structures: Jonah Skoog, Vicki Hoyle, David Page, Jason Gromski

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Cycler – Module Layering & Truss Size

Material Thickness (m)Nomex 0.0010Viton + Water 0.0250Aluminum Hull 0.0052Kevlar 0.0150Polyethylene 0.2500MLI 0.0500Aluminum Shield 0.0020

Large Element Radius – 7 cmSmall Element Radius – 5 cmPassageway Radius – 1 mPassage Wall Thickness – 7.8 cm

AAE 450: Structures: Jonah Skoog, Vicki Hoyle, David Page, Jason Gromski

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Cycler - Structural Weight

Radiation Shielding155,660 kg

Miscellaneous Structure17,580 kg

Docking Bay19,250 kg

Support Structure105,590 kg

Total Structure Mass

142,420 kg37 % of Cycler

Mass

Total Volume 2,790 m3

AAE 450: Human Factors: Wes Dafler, James Pinyerd, Robin Pinson,Mike Sufana

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Internal Layouts

Stairs Down

Computers & Wiring

Trajectory ControlLife

Support EVA

PowerCommunications

All Workstations - 1.829 m x 0.762 m (6.0 ft x 1.5 ft)

Main Frame

Vertical Map Chart

Bookshelves

Access Panel to Crew Quarters

Computers & Wiring

Top Section – Central Command

7.3m x 4.6m x 2.3m (24ft x 15ft x 7.5ft)

Water Processor Assembly

Dresser / Per. StorageC

loset

XL Full BedDesk

Access Panel to Above Room

Sliding Door

Stairs Up

Storage Water Tank

Circular Shower

Waste Collector Subsystem

Bathroom

Fire / O

2

Top and Bottom Sections – Crew Quarters

7.3m x 4.6m x 2.3m (24ft x 15ft x 7.5ft)

Central Meeting Area Galley and Food Preparation Relaxed Environment for

Reading / Games / Movies

Top Section – Kitchen / Entertainment

7.3m x 4.6m x 2.3m (24ft x 15ft x 7.5ft)

Top Section – Medical

4.9m x 4.6m x 2.4m (16ft x 15ft x 7.5ft)

1000 kg of Medical Consumables

Emergency Room Bed / Equipment

Refrigerator for Crew Samples

Bottom Section – Electronics Bay / Back-up Command

7.3m x 4.6m x 2.3m (24ft x 15ft x 7.5ft)

Back-up Computer Consoles Training Simulations Electronics and Hardware for

Repairs

Growing Bay for 60% of Crew’s Food

Morale Booster

Bottom Section – Hydroponics Bay

7.3m x 4.6m x 2.3m (24ft x 15ft x 7.5ft)

Bottom Section – Exercise Module

4.9 m x 4.6 m x 2.3 m (16 ft x 15 ft x 7.5 ft)

Cardiovascular and Strength Training Equipment

Virtual Reality Equipment Arts and Craft Supplies


26

Food & Water

1.http://www.pansophist.com/epbts5.htm

2.http://spacelink.nasa.gov/Instructional.Materials/NASA.Educational.Products/Space.Food.and.Nutrition/station.html3. http://science.nasa.gov/headlines/y2000/ast13nov_1.htm

60% Hydroponics

40% Dehydrated Rations

Total Food Mass: 9120 kg

Daily Food Requirements 2.3 kg / person / day

1

2

3

Daily Water Needs

Hydroponics: 66.0 kg / day

Crew Rations: 4.1 kg / person / day

Hygiene / Appliances: 92.8 kg / day

Total Water Mass: 33610 kg


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Atmosphere Regulation

2BMS Sabatier

ElectrolysisDehumidifierand filters

O2 and N2 Tanks

H2 Tanks

AAE 450: Propulsion: John Gedmark, Mark Kuipers, Joe Sherrick, See-Chen Lee, Emily Vaughan, Geoffrey Osier

28

Cycler Propulsion System Concept

Propulsion system corrects orbit and attitude errors, perturbations

Ion propulsion has: High performance Long lifetimes Good reliability

Distribution allows thrusting at center of mass

Design of thrusters allows precise attitude and trajectory control

AAE 450: Propulsion: John Gedmark, Mark Kuipers, Joe Sherrick, See-Chen Lee, Emily Vaughan, Geoffrey Osier

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Xenon-Ion Thruster Design

0.3 m 1.3 m

Successfully flown on Deep Space One mission Xenon is an inert gas

Minimal interactions Safe

For each thruster: 0.162 N Thrust 170 kg Propellant 5.38 kW Power 6080 s Isp

http://nmp.jpl.nasa.gov/ds1/

AAE 450: Power: Alex Bohnert, Daniel Chakraborty, Cristina Gordon, Yen Ching Yu

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Primary Power Source - Heatpipe Power System

Safe Affordable Fission Engine (SAFE)

Thermal energy to electrical energy through conduction

Reliability: 99.97% per synodic period

Power Needed: 119.5 kW Power Provided: 132 kW

Courtesy of Jonah Skoog

Courtesy of Poston, Kapernick, and Guffee

AAE 450: Power: Alex Bohnert, Daniel Chakraborty, Cristina Gordon, Yen Ching Yu

31

Back Up Power Source - Solar CellsWhy Solar Cells?

ReliableHigh Power-to-Mass RatioNo Consumables

How Do They Work?Convert sun’s photons into electricity

Where Are They?On side of habitats that always

faces the sun.

Reliability98.8% (15 failures in 1274 missions)

Back-up Power Needed: 95 kWMinimum Power Provided: 96.7 kWCourtesy of Jonah Skoog

www.clipart.com

AAE 450: Thermal Control Group: Brandon Owens, Kevin Miller, Eric Briggs, and Chris Dennis

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Thermal Control The problem of heat production

QThrusters

QSUN

QNUKE

QElectronics QPeople

QLoss

CYCLER

TCS

QExcess

QExcess


33

Cycler Thermal Control System Heat capture, transportation, and expulsion system

Water Ammonia

TCS Cycler Interior Cycler Exterior


34

Internal Thermal Control Loop

IFHX

CAHX

IPA

C/P’s and Local HX’s

Air inAir out


35

External Thermal Control Loop

ExVA

Radiators

CPA

T1 T2

Tex

IFHX

Water in Water out


36

34-meter


http://www.aerial.fi/aerial-wlan.pdf

Cycler Communications

Ka-Band

S-Band

Taxi/CargoCycler

AAE 450: Aerodynamics: James Watson, Ravi Mathur, Matt Adkins

37

Approach

2 2.5 3 3.5

x 106

-2

-1.5

-1

-0.5

0

0.5

1

1.5

2

2.5

x 106

Taxi Vehicle Trajectory At Mars

x [m]

y [m

]

Target Periapsis Altitude Capture Window

Mars: 0–35 km Earth: 50-75 km

Direct Entry to Landing Short Time of Flight

Atmospheric Model Assumptions


38

Capture and Entry

Capture Density Dynamic Pressure

Controller Angle of Attack, α

Maximum Lift Bank Angle, β

Lift Vector ControlL/D = 0.36


39

Parachute Deployment Altitude 10 km

Engine Burn Mars Descent

Landing Velocity <10 m/s

Descent and Landing


40

Break #2

BREAK #2

AAE 450: Thermal Control: Chris Dennis, Kevin Miller, Brandon Owens, Eric Briggs

41

Taxi Reentry Heating

Airflow

Stagnation Point

Windward Side

Leeward Side

Nose

We need some way of Absorbing and reflecting away This heat!!!!

Significant heat load Aerodynamic heating

Heat loads are largest at earth.

At stagnation point: Peak heat load is around 1.8

MW/m2 Flux of 1 MW/m2 for around 100 s


42

Taxi Heat Shield

6 mm thick Al2O3 Nosecone (very high temperature material)

Ceramic Tiles (thickness = 10-150 mm) (low density, high performance

material)Borosilicate Glass Coating

Advanced Flexible Reusable Surface Insulation

(10 mm thick thermal blanket)


43

Resulting Temperatures

AAE 450: Propulsion: Mark Kuipers, John Gedmark, See-Chen Lee, Geoffrey Osier, Joe Sherrick, Emily Vaughan

44

Mars Landing and Mars Launch

Mars Landing

98 m/s Final ΔV Drop

60 s Hover Time

Mars Launch

13,000 m/s Total ΔV

250,500 kg GLOM

http://ww

w.m

sss.com/m

ars_images/m

oc/2003/04/04/limb/E

23-00100_lim

b.jpght

tp://

mar

s.jp

l.nas

a.go

v/ga

llery

/vol

cano

es/

PIA

0147

6.ht

ml


45

Nuclear Thermal Rocket Engine

1,060 s Isp 893,430 N Thrust Liquid H2 Propellant 5 rem Radiation Dose


46

Launch Safety

2. Crew Module Separation

1. NTR Engine Shutdown

3. Coast, Reentry, Parachute Deployment

4. Rocket-Assisted Parachute Landing On Mars

Contingency Plan


47

Earth Landing Crew Module Separation Reentry and Parachute Landing

http://community.webshots.com/photo/

5010835/7958663jCdUNLEMZQ


In the Year 2035…

Taxi (2)

Cargo vehicle (4/synodic period)

Tanker (4)

Cycler (4)

Vehicle Images: Jonah Skoog

Planets not to scale

AAE 450: Project Management: Eric Briggs, Laurel Brown

49

Propellant and Risk

Propellant is analogue for maintenance cost.

Major decisions affecting propellant Use of tanker 4-cycler system

Success rate per synodic period: 99% Major contributors to risk

Chemical boosters Vehicle rendezvous Aerocapture and aerobraking

Earth

Mars

Objects weigh 62% less on Mars.

AAE 450: Project Management: Eric Briggs, Laurel Brown

50

Laurel BrownEric Briggs

Brenda EichelJimmy Hidayat

Rebbecca KacvinskyAaron Murphy

Gina PieriAmber Rist

Alex BohnertDaniel Chakraborty

Cristina GordonYen Ching Yu

John GedmarkMark Kuipers

See-Chen LeeGeoffrey Osier

Joe SherrickEmily Vaughan

Matt AdkinsRavi Mathur

James WatsonValerie Kost

Samantha MartinezAndrew Myer

Wes DaflerRobin Pinson

James PinyerdMike SufanaChris DennisKevin Miller

Brandon OwensJason Gromski

Vicki HoyleDavid Page

Jonah Skoog

Back Home AgainThank You for Attending

http://www.cruiseweb.com/HAL-KW-BEACH-PHOTOS.HTM

Documents

AAE 450: Laurel Brown, Project Manager; Eric Briggs, Assistant Project Manager1 AAE 450 Senior Design Formal Presentation aae450