Week 2 - Thursday...2 – Estimate of H2O acquisition, Sabatier, and electrolysis (from In-Situ...

AAE 450

Spring 2011

Week 2 - Thursday

Section 1 Presenting

AAE 450

Spring 2011 Time Presenter Group

8:40 Courtney McManus PM

1 8:45 Alexander Roth Aero

2 8:51 Austin Hasse Aero

3 8:57 David Schafer Att/Con

4 9:03 Paul Frakes Att/Con

5 9:09 Sarah Jo De Fini Comm

BREAK

6 10:35 Trieste Signorino MisDes

7 10:41 Megan Sanders Mis Des

8 10:47 Drew Crenwelge Power

9 10:53 Elle Stephan Power

Break

10 11:10 Jared Dietrich Prop

11 11:16 David Wyant Prop

12 11:22 Michael Hill Prop

13 11:28 Zachary Richardson HF

BREAK

14 11:45 Ben Stirgwolt HF

15 11:51 Andrew Curtiss StrcThrm

16 11:57 Kim Madden StrcThrm

AAE 450

Spring 2011 AAE 450: Courtney McManus

Project Manager Presentation 1:

- Project Timeline

- Rough Cost Estimate

- Mission Timeline

1/20/2011

McManus, Courtney Project Manager

AAE 450

Spring 2011

Design Reviews

Preliminary Design Review

Outline options at a mission level

Show pros and cons of each option

○ Cost

○ Safety

○ Feasibility, etc.

Post PDR decision: mission level options

○ Vehicles

○ Propellant

○ Trajectories, etc


AAE 450

Spring 2011

Design Reviews

Critical Design Review

Outline options at system/subsystem level

Show pros and cons of each option

○ Cost

○ Safety

○ Feasibility, etc.

Post CRD decisions:

○ Total overall look of vehicles, flight phases, etc


AAE 450

Spring 2011

Design Reviews

Final Design Review

Selection of final design from CDR

Includes:

○ Systems

○ Vehicles

○ Configurations, etc

Must make sure everything fits!


AAE 450

Spring 2011

Design Reviews - Dates

TENTATIVE!!!!

PDR: Early February

CDR: Early March

FDR: Late March (after spring break)


AAE 450

Spring 2011

(Very) Initial Cost Estimate


Cost Estimate by Mass Landed on Ceres

Vehicle Mass (kg) Cost (Million USD)

CTV 155000 $155,000.00

ISPP Station 1 3675.6 $3,675.60

ISPP Station 2 3675.6 $3,675.60

Exploration Rover 1 5000 $5,000.00

Exploration Rover 2 5000 $5,000.00

Emergency Rover 4000 $4,000.00

TOTAL: $176,351.20

1

2

2

3

3

3

1 – Estimate of 200 metric tons, minus 45 metric tons of fuel used in transfer

2 – Estimate of H2O acquisition, Sabatier, and electrolysis (from In-Situ Utilization of Indigenous Resources, D. Rapp, 2007

3 – Estimated from NASA’s Space Exploration Vehicle (SEV) as a baseline – www.nasa.gov

AAE 450

Spring 2011

Mission Time Line


AAE 450

Spring 2011

Roth, Alexander Aerodynamics

AAE 450

Spring 2011 Historical Data – Mars Exploration

Rovers (MER) Entry Mass:

Spirit = 827.0 kg

Opportunity = 832.2 kg

Mars Gravity

g = 0.38

Mars Atmosphere Density

P = 0.699*e-0.00009*h kPa


MER Aeroshell Dimensions (Data From P. Desai & P. Knockle,“Mars Exploration Rovers Entry, Descent, and Landing Trajectory Analysis”)

AAE 450

Spring 2011 Historical Data – MER Trajectory

Simulation Data Hypersonic Flight (tentry = 0 sec) ―Spirit‖ Mean ―Opportunity‖ Mean

Peak Heating Rate (W/cm2) 39.9 42.2

Attitude @ Peak Heating Rate (deg) 0.6 0.6

Peak Acceleration (Earth g) 5.9 6.4

Peak Stag Pressure (N/m2) 9984 10835

Total Heat Load (J/cm2) 2770 2711


Parachute Deployment (tentry = 245.6 sec) (tentry = 242.1 sec)

Mach Number 1.78 1.86

Dynamic Pressure (N/m2) 724.2 747.0

Attitude (deg) 1.1 1.0

Heat Shield Jettison (tentry = 265.6 sec) (tentry = 262.2 sec)

Mach Number 0.47 0.42-0.56

Dynamic Pressure (N/m2) 60.8 63.5

(Data From P. Desai & P. Knockle,“Mars Exploration Rovers Entry, Descent, and Landing Trajectory Analysis”)

AAE 450

Spring 2011

Austin Hasse

AAE 450: Week 1 Presentations

1/29/2011

Job Description

Aerodynamics Group Leader

Examine different concepts for re-entry into Earth atmosphere

Tasks

Investigate Ballute Aerocapture

Simple calculations based on previous studies

Hasse, Austin Aerodynamics

AAE 450

Spring 2011

• Avoid the high heat

rates on spacecraft

• Mass fraction of 10-

15% compared to

propulsion re-entry

• Can be stowed in a

small volume and

inflated

Ballute Aerocapture


Sketch of Trailing Ballute

AAE 450

Spring 2011

Inputs

Given entry velocity

between 6-8 km/s

Mass of spacecraft

~1000kg

Outputs

Mass of Ballute ~75kg

(propellant mass ~

500kg)

Surface area ~ 750m2

Volume - minimal

deflated volume

Results


AAE 450

Spring 2011 AAE 450: David Schafer

Attitude Control Presentation 1: Artificial Gravity

1/20/2011

Schafer, David Attitude Control

AAE 450

Spring 2011

Basic (Simplest) Concept Counter-rotating Concept

Artificial gravity Modeling


AAE 450

Spring 2011

Minimum Radius Minimum Gravity Differential

Maximum spin rate given

as 6 revolutions per

minute*.

Sets minimum radius at 9.4

meters.

Outward acceleration

changes by .08 g’s in 2

meters (that is over twice

the gravity of Ceres).

Setting outward

acceleration change to

.028 in 2 meters

Sets radius at 27 meters

Provides spin rate of 3.5

revolutions per minute.

Providing Artificial Gravity


* Maximum human spin rate comes

from Young, L., and was checked

with Human Factors group

AAE 450

Spring 2011 Paul Frakes


Tasks Accomplished:

Met with group to discuss possible

configurations, possible control technologies

Compared masses of control technologies

in existing spacecraft

Provide mass of ADCS as percentage of total

mass

Frakes, Paul Attitude Control (ADCS)

AAE 450

Spring 2011

Liquid propellant engines – hypergolic bipropellant,

monopropellant; no cryogenics

Spin stabilization – artificial gravity in Transfer Vehicle

Reaction wheels – allow precise control, require

momentum dumping

Control Moment Gyroscopes (CMGs) – less power

than reaction wheels, no momentum dumping

Passive control systems – gravity gradient

stabilization, magnetic torquers

Attitude Control Systems

Considered


AAE 450

Spring 2011

Apollo CM

Hypergolic propellants

6.9% of total S/C mass

STS APU

Hydrazine engines

0.5% of total orbiter

mass

ISS CMGs

0.3% of total mass

Does not include

reaction thrusters

Results


New Horizons

Hydrazine


Includes trajectory

correction thrusters

Dawn

Reaction wheels and

hydrazine engines


AAE 450

Spring 2011

Communications

Sarah Jo DeFini

Task: Research Ceres Orbiting

Communication System Options

AAE 450

Spring 2011

Preliminary Design Requirements

Ceres Ground Stations must be able to

communicate with each other, with the Crew

Transfer Vehicle, and with the Exploration

Rovers at all times

Redundancy is desirable

All communication links must support two

HDTV channels and telemetry data

DeFini, Sarah Jo Communications

AAE 450

Spring 2011

One satellite will not

be able to cover more

than 40% of the

surface at any given

time (from a circular

orbit)

Begin Link budget

calculations for a 100

Mbps link to a satellite

in a 15,000 km orbit

Numbers and Next Steps

DeFini, Sarah Jo Communications

AAE 450

Spring 2011

BREAK – See you at 10:30!

AAE 450

Spring 2011

Signorino, Trieste Mission Design


AAE 450

Spring 2011

• Assumptions:

• Thrust: 5 – 10 N

• ISP = 2000 s

• Mass at Escape (mf ) ≈ 100 metric tons

Elliptic Spiral Escape


Thrust (N) m0 (metric tons)

mf (metric tons)

mprop (metric tons)

TOF (yr)

10 150 93.723 56.277 3.5

9 175 102.645 72.355 5

8 175 97.821 77.179 6

7 175 107.468 67.532 6

6 150 92.116 57.884 6

5 - - - >6

AAE 450

Spring 2011

Mission Implementation

Cargo and Communication Satellite Launches

Use for crew rendezvous just prior to escape

Future Work

Determine more accurate time of escape

Determine rendezvous information for crew mission

Combine with impulse to make hybrid to Ceres

Implementation and Future Work


AAE 450

Spring 2011

Megan Sanders


Tasks Accomplished:

Research

Escape Trajectory – Circular Spiral

Sanders, Megan Mission Design

AAE 450

Spring 2011

• Escape Mass of

100 metric tons

• Escape radius

of 1.5 million km

• 5-15 N thrust

range

• Start from LEO

Technical Details

Sanders, Megan Mission Design

-8 -6 -4 -2 0 2 4 6

x 105

-6

-4

-2

0

2

4

x 105

X Position (km)

Y P

ositio

n (

km

)

Escape Spiral

LEO

AAE 450

Spring 2011

Propellant mass of 45 metric tons

Time of Flight is 2-3.5 years

Increasing thrust reduces TOF but

increases propellant mass

Approximately linear relationship

between escape mass and TOF

Results

Mission Design Sanders, Megan

AAE 450

Spring 2011 Drew Crenwelge 20 January 2011

Power Group:

Nuclear Power Possibilities

Crenwelge, Drew Power Group

AAE 450

Spring 2011

Radioisotope Generator, (RTG)


Advanced Stirling

RTG

Multi-Mission

RTG

Power Output (Wt) 500 2000

Power Output (We) 110 -140 100 - 125

System Mass (Kg) 20.9 43

Fuel Mass (Kg) 0.8 ~3.2

Specific Power (W/kg) ~6.7 ~2.8

Dimensions (cm) 72.4 x 45.7 x 29.2 64 x 66 (cylinder)

Mission Life (Years) 14-17 14-17

Operating Temperature

Differential (Celsius)

50 – 650

90 – 850

50 - 650

AAE 450

Spring 2011

Nuclear Fission Reactor


HOMER-15

(U.S)

SP – 100

(U.S)

SAFE – 400

(U.S)

TOPAZ

(Russia)

Power Output (kWt) 15 2000 400 150

Power Output (kWe) 3 100 100 5-10

System Mass (Kg) 214 5422 1200 320

Fuel Mass (Kg) 72 (UN) 140 (UN) 512 (UN) 12 (UO2)

Specific Power (W/Kg) 14.02 18.44 83.33 23.44

Core Temp. (Celsius) 600 1377 1020 1600

Core Dimensions (cm) 18 x 36 37 x 75 30 x 50 ? X ?

Future Work:

• Explore more fission reactor possibilities

•Couple Stirling Engine with fission reactor for more efficiency?

Courtesy of G.L Kulcinski’s “Nuclear Power in Space”

AAE 450

Spring 2011 Elle Stephan 20 January 2011

Power Group:

Solar Arrays

Stephan, Elle Power

AAE 450

Spring 2011

Known Capabilities

Solar Array Variations

ISS Magellan Orion

Vehicle Type Crew Module Probe Crew Module

Mass (kg) 375,727 1035 21,250

Shape 8 wings 2 sq panels 2 circular

Power

(W/m²)

2400 100 1833

Battery NiH_2

NiCad Li-ion

Stephan, Elle Power

AAE 450

Spring 2011

Solar Limitations

Stephan, Elle Power

Distance from Sun (AU) Power Output (W/m²)

1(Earth) 250

1.5 (Mars) ≈ 219.8

2.8 (Ceres) ≈ 141.1

5 (Jupiter) 8.1

*Using a solar array area of 60m²

Future Work:

• Continue work on various battery options

• Research into the benefits of fuel cells

AAE 450

Spring 2011

BREAK!

Start again at 11:10

AAE 450

Spring 2011 Jared N Dietrich 1/20/2011

AAE 450: Week 1 Presentations Propulsion, CAD

Tasks Accomplished:

Group Meeting – Research areas assigned

Launch Vehicle Trade Study

Data Analysis – Mass, Thrust, Cost, Reliability

Dietrich, Jared N Propulsion

AAE 450

Spring 2011

Launch Vehicle Options


Vehicle Thrust (kN) Payload to LEO (kg)

Ares I1 17,180 25,400

Ares V2 32,6306 188,000

Falcon 93 4,940 10,450

Falcon 9H4 15,000 32,000

Atlas V (401)5 8,590 12,500

Atlas V (H)8,9 12,654 29,400

Falcon 9 (Credit: SpaceX11) Atlas V (Credit: NASA12)

Ares I, V (Credit: NASA13)

AAE 450

Spring 2011

Launch Cost per kg: Ares I……………$5,433/kg

Ares V…………..$1,862/kg

Falcon 9………...$5,359/kg

Falcon 9H………$2,969/kg

Atlas V………….$14,960/kg

Atlas V HLV…….$8,899/kg

Results


$0

$2,000

$4,000

$6,000

$8,000

$10,000

$12,000

$14,000

$16,000

1 2 3 4

Ares 1 Falcon 9

Atlas V

Ares V Falcon 9H

Atlas VH

(Normal)

(Heavy)

0%

20%

40%

60%

80%

100%

1

100%

0

100%

0

96%

0

Ares I

Ares V

Falcon 9

Falcon 9H

Atlas V

Atlas VH

Launch History Ares I………………..1/1

Ares V……………….0/0

Falcon 9…………….2/2

Falcon 9H…………..0/0

Atlas V………………22/23

Atlas V HLV…………0/0

AAE 450

Spring 2011 David Wyant

Jan. 20, 2011

Group: Propulsion

Hover Requirements and Rover Propulsion

Wyant, David Propulsion

AAE 450

Spring 2011

Est. Mass: 30,000 kg

Hovering

Prop. Mass: 125 kg

Thrust: 8,644.3 N

Ascent

Delta V: 0.342 km/s

Prop. Mass: 2,650 kg

Will require ability to

deep throttle engine

Based on CECE by

Pratt & Whitney

Hovering Lander Requirements


0

500

1000

1500

2000

2500

3000

3500

4000

4500

5000

0 20000 40000 60000

Pro

pellan

t M

ass (

kg

)

Vehicle Mass

Propellant Mass Trends

Ascent Propellant

Hover Propellant

AAE 450

Spring 2011

Drive System Req. Power

or Thrust

Req. Motors Mass Propellant

Mass

Tracked or

Wheeled

530.9 W 1-4 5 – 20 kg

(5 kg/motor)

N/A

Chemical

Rocket

(100 N)

500 N 5 18.5 kg

(3.7 kg/motor)

9,000 kg

Ion Thrusters

(1.5 N)

500 N 318 1,685.4 kg

(5.3 kg/motor)

1,630 kg

Rover Propulsion System


Est. Mass: 420 kg

Max Payload: 1320 kg

Top Speed: 100 km/hr

AAE 450

Spring 2011 Michael Hill

AAE 450: Week 1 Presentation Team Tasks:

Propulsion Group Leader

Examining Earth to Ceres Propulsion

Hill, Michael Propulsion

AAE 450

Spring 2011

• Maximum

Payload per ΔV.

• From LEO with

Ares V (max

188,000 [1] kg

payload)

• Isp = 448 sec [2]

finert = 0.08 [3]

• Hohmann

Impossible

Impulse from J-2X Engine


AAE 450

Spring 2011

Nuclear [4] (NERVA)

Isp = 825 sec

Thrust ~ 334,000 N

Requires ~ 1590 kg of

shielding

Engine Mass = 10,138

kg

Generates 1570 MW

Hohmann Still not

possible

Electric [5] (VASIMR)

Isp ~ 3000-5000 sec

Thrust ~ 5 N

200 kW req. per engine

Runs at 60% efficiency

Electric and Nuclear Options


AAE 450

Spring 2011

Zachary Richardson

Week 1 Presentation: 1/20/2011

Group Lead: Human Factors & Science

- Optimization Code

- Life Support Requirements

Tasks Accomplished:

Organized HFS group and brainstormed

Developed code for optimization help

Did generalized calculations for food, water, air

Richardson, Zachary Human Factors & Science

AAE 450

Spring 2011

Mission Time Effects


0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

0 10 20 30

Mass (

kg

)

Mission time (months)

Mass vs. Mission Time 6 – 70 months

Assumptions

Food,

Water, Air

Vehicles

Regenerative

Aspects

AAE 450

Spring 2011

Upcoming Tasks Separate Mass, Power, Volume into different vehicles and

expand detail analysis of previous aspects

Determine science needed for ISPP and other science equipment critical for mission

Results (CTV)


Variable Mass (kg) Power (kW)

(ISS* values)

Volume (m^3)

Food 787 - 3800 3.01 – 4.26 3.1 - 14.8

Water 3180 - 12000 .545 3.2 - 12.3

Air 220.4 - 235 1.45 183.1 - 194.8

Total: 5000 - 19000 100** 186.2 - 207

AAE 450

Spring 2011

BREAK!

Start again at 11:45

AAE 450

Spring 2011 Ben Stirgwolt AAE 450: Week 1 Presentations

Human Factors & Science:

Crew Transfer Vehicle (CTV) Artificial Gravity

CTV Radiation Protection

Stirgwolt, Ben Human Factors & Science

AAE 450

Spring 2011


Artificial Gravity

Rota

tional R

adiu

s,

R (

m)

10

100

1000

Human Comfort Zone

0.1 10 4.0

Angular Velocity, Ω (rpm) 1.0 2.0 3.0

Comfortable, 5 of 5 researchers



Optimal

From a

Human Factors

perspective:

Ω = 2.0 rpm

R = 84.95 m

Possible

Ω = 3.0 rpm

R = 37.76 m

Probably Not

Ω = 4.0 rpm

R = 21.24 m

Figure based on Hall, Ref. 1

AAE 450

Spring 2011

Radiation Protection


Radiation Source Amount (Sieverts—SV)

Galactic Cosmic Radiation (GCR) .60 Sv/year

Solar Particle Event (SPE) 4.5 Sv/day

Trapped Radiation .0005 SV/day

Manmade Sources

(i.e. radioisotropic power generators) N/A

Values based on “Spaceflight Radiation Health Program at JSC,” Ref. 2

Blood forming

organs Eyes Skin

Annual Exposure

Limit (SV) .5 2 3

AAE 450

Spring 2011

Andrew Curtiss

Structures & Thermal

-Website setup

-Crew Capsule Dimensional Analysis

-Artificial Gravity Analysis

Curtiss, Andrew Structure & Thermal

AAE 450

Spring 2011

Crew Capsule Dimensions -Optimized for Minimum Surface Area

-Meets Artificial Gravity Requirement

-Meets Crew Quarters Volume Requirements

*Dimensions are for the crew capsule only – no storage volume

Radius = 3.06 Meters

Height = 6.12 Meters

Surface Area = 176.48 Meters2

RPM = 10.55

Volume = 180 Meters3

r

h


AAE 450

Spring 2011

Bottom Line:

-Creating artificial gravity by spinning crew capsule on

its axis is NOT FEASIBLE

-Capsule needs larger rotational radius to

keep crew healthy

-Can use optimized dimensions for crew capsule on

previous slide


AAE 450

Spring 2011

Kim Madden

Structures & Thermal Control

-Manage S&TC Calendar

-Ceres Regolith Containment

-Material Options

Madden, Kim Structure & Thermal

AAE 450

Spring 2011

Ceres Regolith Container Size •Density: 2.2 g/cm3 [1, 2]

•Average Volume Required = 0.4578 m3

•1000 kg of regolith

•Useable Volume = 0.6867 m3

•Added 50% to calculated volume to account for free

space (air) between samples (approximated)

•Different Storage Configurations

•Cube: 0.8822 m x 0.8822 m x 0.8822 m

•Surface Area: 4.6700 m2

•Cylinder: Radius = 0.4800 m, height = 0.9487 m

•Surface Area: 4.3087 m2

Madden, Kim Structure & Thermal

AAE 450

Spring 2011 Material Study [3]

Material Density

(kg/m3)

Young’s

Modulus (GPa)

Yield Stress

(MPa)

Ultimate

Stress (MPa)

Aluminum Alloy:

7075-T6

2,810 72 480 550

Aluminum Alloy:

2014-T6

2,800 73 410 480

Aluminum Alloy:

2090-T83

2,590 76 520 538

High Strength Steel 7,850 190-210 340-1,000 550-1,200

Radiation Shielding Material

-Aluminum

-Polyethylene: high H content

absorbs/scatters radiation,

absorbed 20% more than aluminum Madden, Kim Structure & Thermal

Week 2 - Thursday...2 – Estimate of H2O acquisition, Sabatier, and electrolysis (from In-Situ...

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Transcript of Week 2 - Thursday...2 – Estimate of H2O acquisition, Sabatier, and electrolysis (from In-Situ...