Week 4 Thursday (2/3) · Ares V C&C Launch Vehicle Spring 2011 ARES V C&C LAUNCH VEHICLE – SPECS...

AAE 450

Spring 2011

Week 4 – Thursday (2/3)

Courtney McManus

AAE 450

Spring 2011

Today’s Schedule

Review of Schedule

Pass out MDRs

Section 1 Presentations

Prof Longuski

Discussion of MDRs

C. McManus Project Manager 2/3/2011

AAE 450

Spring 2011

Semester Schedule

McManus, Courtney Project Manager 2/3/2011

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

2/3/2011

AAE 450

Spring 2011 Alexander Roth

AAE 450: Week 4 Presentations Aerodynamics & CAD

Vehicle Groups:

Cargo Launch Vehicle

Crew Launch Vehicle

Crew Transfer Vehicle

Tasks Accomplished:

Developed code for aerocapture trajectories

Developed code for lower altitude density

Roth, Alexander Aerodynamics & CAD

AAE 450

Spring 2011

Aerocapture

Spacecraft makes one pass through the

atmosphere

Altitudes Tested:

h = 65-100 km

V∞ = 10.885 km/s (Hohmann Transfer)

VLEO = 7.699 km/s

mctv = 250 tons

SCTV = 1000 m2

CD,CTV = 2.07


Hyperbolic

Approach

(1) Aerocapture

Maneuver

(at altitude h)

(2) Periapse

Raise Maneuver

(LEO - Final Orbit)

AAE 450

Spring 2011

Aerocapture Results

Altitude, h

(km), @ (1)

Atmospheric

Density, ρ

(kg/m3), @ (1)

Velocity After

Aerocapture

(km/s), @ (2)

∆V Needed for Periapse

Raise Maneuver (to LEO)

(km/s), @ (2)

65 7.2617e-5 8.0214 -0.3218

70 3.2993e-5 11.2564 -3.5568

75 1.4990e-5 12.4870 -4.7874

80 6.8108e-6 12.9573 -5.2577

85 3.0945e-6 13.1449 -5.4453

90 1.4059e-6 13.2062 -5.5066

95 6.3879e-7 13.2279 -5.5283

100 2.9023e-7 13.2542 -5.5546


Aerocapture orbit fails at h < 65 km

Aerocapture actually increases CTV’s velocity at h > 70km (sling shot)

V∞ = 10.885 km/s & VLEO = 7.699 km/s

AAE 450

Spring 2011 Austin Hasse

AAE 450: Week 2 Presentations

2 / 3 / 2011

Job Description

• Aerodynamics Group Leader

• CTV Group Member

• Earth Ascent/Re-entry Group Member

Tasks

• Calculate Ballute Sizing For Earth Aerocapture

• Model Ballute in CATIA

Hasse, Austin Aerodynamics 2/3/2011

AAE 450

Spring 2011

CTV Aerocapture Ballute

CTV mass 155 tons

Kapton Material developed by DuPont

Outer Radius – R_t = 100.5 m

Tube Radius – r_t =25.1 m

Hasse, Austin Aerodynamics 2/3/2011

AAE 450

Spring 2011

Ballute Mass = 1.26 tons

Compressed Volume = 0.9

m^3

Expanded Surface area =

126,730 m^2

Results

Hasse, Austin Aerodynamics

Future Work

Refine Ballute Sizing

given more precise

CVT mass

Analyze heating

rates throughout

trajectory

2/3/2011

AAE 450

Spring 2011

AAE 450 Section 1 David Schafer

Attitude Control

Presentation 2:

Satellite and Landing Control

2/3/2011

AAE 450

Spring 2011

Satellite Control

Fine

Guidance

Sensor

Motion

Reference

Unit

Reaction

Wheel

Control

Moment

Gyroscope

Mass

[kg]

5 2 10 100

Power

[Watt]

20 5 1,000,000 500

Sensors Actuators

Schafer, David 2/3/2011

AAE 450

Spring 2011

2/3/2011

Landing Control

Mass [kg] 30,000 50,000 100,000

Thruster

offset 1°

1,400 Nm 2,400 Nm 4,800 Nm

Thruster

offset 5°

7,000 Nm 12,000 Nm 24,000 Nm

Thruster

offset 1°

7,000 Nm 12,000 Nm 24,000 Nm

Thruster

offset 5°

35,000 Nm 60,000 Nm 120,000

Nm

Radius = 10 m Radius = 50 m Schafer,

David

AAE 450

Spring 2011 Paul Frakes


Tasks Accomplished:

Start to consider non-gravitational,

environmental space torques

Van Allen belt particle collision

Solar radiation

Frakes, Paul Attitude Control (ADCS) 2/3/2011

AAE 450

Spring 2011

Assume:

250 days in Van Allen belts

Vehicle modeled as cylinder, r = 10 m, h = 100 m

Attitude Control Engine Isp = 200 s

S/C speed = 8000 m/s

Total Impulse: 54.25 N s

Propellant mass: 0.27 kg (negligible at this point)

Cargo Transfer Vehicle


AAE 450

Spring 2011

Assume

2 yr transit time

Same dimensions, Isp

Average distance of 2.5 AU

Total Impulse = 21600 N s

Propellant Mass = 108 kg



AAE 450

Spring 2011

Communications

Sarah Jo DeFini

Ceres-Orbiting Communications Satellites

Cargo Launch Vehicle


AAE 450

Spring 2011

• Orbits considered:

Ceres-

synchronous,

Molniya, Tundra

• All are relatively

low altitude

• 3 Satellites

required minimum

(2 for halo orbits)

Ceres-Orbiting Satellites

DeFini, Sarah Jo Communication

AAE 450

Spring 2011

RF HDTV signal from

Orbiting Satellites to

Ceres Surface:

Power: 3-5 kW

Ground Dish size: 3-4 m

Next time:

Research specific

equipment required

(dish mass and volume)

Begin Link Budget for

CTV and CLV

Numbers and Next Steps

DeFini, Sarah Jo Communication

Generated using code from Tony D’Mello

AAE 450

Spring 2011

See you downstairs at 10:30!!

2/3/2011

AAE 450

Spring 2011

Signorino, Trieste Mission Design


Vehicle Groups:

- CTV Launch

- Communication Satellites

AAE 450

Spring 2011

• Assumptions: • Two Engines: Low Thrust and Kick Engine

• Isp = 5000s for Low Thrust and Isp = 450s for Kick

• ∆V at Earth is from LEO of 350 km

• mprop = mprop_transfer + mprop_kick

CTV Spiral to Ceres


• Best run for lowest ∆Vtot •∆Vtot = 4.035 km/s

•T = 59 N

•TOF = 1.85 years

•mprop = 370 metric tons

• Best run for lowest TOF •∆Vtot = 9.32 km/s

•T = 20 N

•TOF = 0.72 years

• mprop = 448 metric tons -3 -2 -1 0 1 2 3

-2.5

-2

-1.5

-1

-0.5

0

0.5

1

1.5

2

2.5

X Distance (AU)

Y D

ista

nce (

AU

)

CTV Spiral Transfer - Trieste Signorino

Earth Orbit

Ceres Orbit

Transfer Orbit

2/3/2011

AAE 450

Spring 2011


Thrust (N) TOF (yrs)

∆Vceres (km/s)

∆Vearth

(km/s)

∆Vtot (km/s)

mprop (metric tons)

60 1.41 1.56 4.09 5.65 415

55 1.42 1.78 4.04 5.83 417

50 1.39 2.4 4.23 6.63 434

45 1.39 2.6 4.28 6.88 435

40 1.39 2.74 4.38 7.12 436

35 1.40 3.00 4.40 7.40 438

30 1.40 3.25 4.47 7.72 440

20 1.39 3.80 4.58 8.38 442

CTV Spiral to Ceres

Future Work:

• Combine with spiral escape for more accurate ∆V’s

• Investigate different steering laws

• Work with propulsion to update engine info and ∆V info

2/3/2011

AAE 450

Spring 2011

Megan Sanders

AAE 450: Week 4 Presentations Tasks Accomplished:

Circular and Elliptical Spiral Comparison

Crew Rendezvous

Sanders, Megan Mission Design 2/3/2011

AAE 450

Spring 2011

Crew Rendezvous

Sanders, Megan Mission Design

•Elliptical rendezvous

performed at

periapsis

•Circular rendezvous

performed at ¾ of a

rotation

•Both rendezvous

calculated for last

spiral before escape

0

10

20

30

40

50

60

70

80

De

lta V

(km

/s)

Tra

nsfe

r Tim

e (d

ays)

Tota

l Hu

man F

light

(days)

Circular

Elliptical

2/3/2011

AAE 450

Spring 2011

Summary

Similar in delta v, human flight time, radiation

Circular – shorter total time

Elliptical – shorter transfer time

Recommendations

Elliptical for crew

Circular for cargo

Radiation

Mission Design Sanders, Megan

10 10.5 11 11.5 12 12.5 13 13.5 14 14.5 15240

260

280

300

320

340

360

380

Thrust (N)

Tim

e (

days)

Circular

Elliptical

2/3/2011

AAE 450

Spring 2011 Drew Crenwelge 03 February 2011

Power Group: Regenerative Fuel Cells

CTV and Rover Power (Solar,Nuclear,Chemical)

Crenwelge, Drew Power Group 2/3/2011

AAE 450

Spring 2011

Regenerative Fuel Cells

Crenwelge, Drew Power Group

Consumes:

0.55 kg H2 /Day

4.77 kg O2 /Day

Produces:

5.1 kg H2O /Day

2/3/2011

AAE 450

Spring 2011

CTV & Rover Results

Crenwelge, Drew Power Group

Crew Transfer Vehicle

(CTV)

Exploration/Rescue

Rovers

Power Required (kW) ~85 – 100 ~13-15

Recommendations:

•For CTV: Solar Power

+ NiH2 Batteries or

Unshielded SAFE-400.

•For Rovers: Fuel Cells

= Simplicity, Reliability.

2/3/2011

AAE 450

Spring 2011

Elle Stephan 3 February 2011

Power Group:

Communication Satellites & ISPP

Stations

Stephan, Elle Power

AAE 450

Spring 2011

Communication Satellites

Stephan, Elle Power

Satellite Relay Ceres

Power Required [kW] 50 80

Power Output [kW/m^2] 1.353 .758

Array Area [m^2] 37 106

Array Mass [kg] 31 89

• Gallium based ZTJ PV cell

Li-ion Battery: 2 – 3 for a 12 yr satellite life

AAE 450

Spring 2011

ISPP Stations

Stephan, Elle Power

Power Required for:

Propellant 0.53 kW/kg

Hydrogen 1857 kW

Oxygen 14840 kW

Power Output [kW]

day 12

4 years 17088

6 years 25632

* At least 2 fuel cells

AAE 450

Spring 2011

Start again at 11:10

2/3/2011

AAE 450

Spring 2011 Jared N Dietrich 3 February 2011

AAE 450: Week 2 Presentations Groups: • Propulsion

• Cargo Transfer Vehicle (CTV)

• CAD

Tasks Accomplished: • Launch Vehicle Determined

• CTV Propulsion Options

• Data Analysis – Mass, Thrust, Power, Isp

34 Dietrich, Jared N Propulsion

AAE 450

Spring 2011

Ares V C&C Launch Vehicle ARES V C&C LAUNCH VEHICLE – SPECS

Thrust 32,6306 kN

ISP,SL 360.82 sec

Total Mass 3,704 mT

Payload Mass 188 mT

Usable Volume 860 (1,410)1 m3

Human Rating RS-68B In Progress3

35 Dietrich, Jared N Propulsion

Ares V Configuration Sketch – Jared Dietrich

(Credit: Phil Sumrall, NASA2) Ares V Shroud Options – Jared Dietrich

(Credit: Steve Screech, NASA1)

AAE 450

Spring 2011

36

Cargo Transfer Vehicle (CTV) (Solar Electric Propulsion)

Dietrich, Jared N Propulsion

• Preliminary Analysis of Electric

Propulsion Systems

• Code using SPT-100 Hall

Thruster4:

Results of Four Hall Thrusters

Prop Mass 500 kg

Mass Ratio 1.48

Delta V 5,828 m/s

Power 1.4 kW

ISP 1,600 s

Burn Time 0.79 yrs

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

0 1 2 3 4

Delt

a V

(m

/s)

Burn Time (years)

Delta V vs Propellant Mass SPT-100 Hall Thruster

OneThruster

TwoThrusters

ThreeThrusters

FourThrusters

AAE 450

Spring 2011 David Wyant

February 3, 2011

Technical Group: Propulsion

Vehicles: Rovers, Cargo Transfer Vehicle

Tasks Accomplished

Met with both vehicle and technical groups

Performed comparison study of rover

propulsion systems.

Wyant, David Propulsion 2/3/2011

AAE 450

Spring 2011

Mass of Propulsion Systems

Wyant, David Propulsion

Travel Times:

Wheeled: 7 days Hopper: 0.65 hours(1 hop) Hovercraft: 1 hour

2/3/2011

AAE 450

Spring 2011

System Power

Req’d

Mass

Wheeled 13 kW 28 kg

Hopper N/A 759 – 988

kg

Chemical

Rocket

Hovercraft

N/A 1539 –

18201 kg

Electric

Thruster

Hovercraft

618 kW 2462 –

5492 kg

Numbers to left at

fastest travel time for

entire range of rover

mass

Recommendations:

Hopper style vehicle for

Rescue Rover

Wheeled or tracked

vehicles for exploration

rovers

Review and Recommendations

Wyant, David Propulsion 2/3/2011

AAE 450

Spring 2011 Michael Hill

AAE 450: Week 2 Presentation Team Tasks:

Propulsion Group Leader

Examining Earth to Ceres Propulsion

Hill, Michael Propulsion 2/3/2011

AAE 450

Spring 2011

LH2/LOX Boost from LEO

𝐼𝑠𝑝 = 450 sec[2]

𝜀 = 60

𝑃𝑐 = 13 𝑀𝑃𝑎

Hill, Michael Propulsion

𝒎𝟎 = 𝟓𝟎𝟎 𝒕𝒐𝒏𝒔 𝑺𝒕𝒂𝒈𝒆𝒔 ∆𝑽 = 𝟒 [𝒌𝒎

𝒔] ∆𝑽 = 𝟔[

𝒌𝒎

𝒔] ∆𝑽 = 𝟖 [

𝒌𝒎

𝒔]

𝑚𝑝𝑎𝑦 [𝑡𝑜𝑛𝑠] 1

~176.1[1] ~96.13[1] ~45.26[1]

𝑚𝑝𝑟𝑜𝑝 [𝑡𝑜𝑛𝑠] 323.9 403.87 454.74


~182.4[1] ~107.6[1] ~62.05[1]

𝑚𝑝𝑟𝑜𝑝 [𝑡𝑜𝑛𝑠] 317.6 392.4 437.95


~184.0[1] ~110.1[1] ~65.22[1]

𝑚𝑝𝑟𝑜𝑝 [𝑡𝑜𝑛𝑠] 316.0 389.9 434.78

2/3/2011

AAE 450

Spring 2011

Low Thrust, VASIMR

Trajectory group – 6000 Isp @ 59 N

Thrust ≈ 5.448 N/engine[3]

Require 11 Engines @ 200 kW

Total Power Requirement = 2.2 MW

Hill, Michael Propulsion 2/3/2011

AAE 450

Spring 2011

Zachary Richardson Week 4 Presentation: 2/3/2011

Group Lead: Human Factors & Science

- ISPP Facility Research

- Seismology

Tasks Accomplished:

Researched processes of ISPP facility

Developed concept for Ceres ISPP production

Generated ISPP production rates and parameters

Created Seismometer placement concept

Richardson, Zachary Human Factors & Science 2/3/2011

AAE 450

Spring 2011

ISPP Facility Production Specs

Richardson, Zachary Human Factors & Science

CI Chondrite: Avg Density = 160kg/m^3

Efficiency Factors of 90% for regolith extract and 80% for electrolysis

Furnace specs:

~300°C

83kW

ISPP Production Totals assuming 1 ton of

regolith is collected per day.

Material Amount

Needed in

2 years (kg)

Gathered

per Year

(kg)

Total days

required at

above rate

Water

8000 9855 297

Hydrogen TBD 876 TBD

Oxygen (Just for crew)

1200 7010 63

2/3/2011

AAE 450

Spring 2011

Upcoming Tasks Determine Hydrogen rates for ISPP facility and power consumption of

electrolysis

Containment method for ISPP facility needs to be further researched

Seismometers: Placement

Richardson, Zachary Human Factors & Science

4 seismometers

placed equidistant

~985km apart

Probe launched from

satellite

Mass: 10kg

Impact speed: 125m/s

CERES

Seismometer

Seismometer Seismometer

120 °

2/3/2011

AAE 450

Spring 2011

Start again at 11:50

2/3/2011

AAE 450

Spring 2011 Ben Stirgwolt AAE 450: Week 4 Presentations

Human Factors & Science:

Rover Specifications

Bioregenerative Life Support Systems

Stirgwolt, Ben Human Factors & Science 2/3/2011

AAE 450

Spring 2011

Stirgwolt, Ben Human Factors & Science

Rover Specifications

Rover Mass (kg) Volume (m3) Power (kW)

Exploration 2592 29.89 9.02

Rescue 636 9.93 2.52

Exploration: 4 crew members; 4 days; areas for galley, lavatory, science equip.

Rescue: 4 crew members; 1 day

Note: Totals are for Human Factors-related

items only (i.e. life support systems)

2/3/2011

AAE 450

Spring 2011

Hydroponics

Stirgwolt, Ben Human Factors & Science

Pros

• ~1000 kg of food

in 2 years

• Psychological

benefits

• Redundancy for

air & water recycle

systems

Cons

• Large mass cost

• Requires ~20 m3 of

CTV volume

• Requires ~15 kW

2/3/2011

AAE 450

Spring 2011

Andrew Curtiss

Structures & Thermal

-Maintain website

-Earth Ascent/Re-entry Vehicle Group

-Cargo Transfer Vehicle Group

-Cargo Launch Vehicle Group

2/3/2011

AAE 450

Spring 2011

r

Re-Entry Heat Shield Possibilities

Shielding Type Mass

(MT/m2)

Power (kW) Reliability Complexity

(Scale 1-10, 10 = High)

AVCOAT 5026-

39

~0.0175 0 10 1

Space Shuttle

Tiles

~0.0110 0 7 4

Reinforced

Carbon-Carbon

~0.0189 0 9 2

Inflatable Kevlar

Shielding

~0.062

Some 6 5

2/3/2011

AAE 450

Spring 2011

EDV Heat Shielding Recommendation:

AVCOAT 5026-39

- Most reliable

- Least complex (no moving parts)

- Proven technology

- Used on Apollo Capsules

- Planned for use on Orion capsule

- Most robust

Estimated Mass: 3.097 MT

Estimated Volume: 6.12 m3

Zero Power Consumption

Drawing based on diagram in ”Apollo Experience

Report – Thermal Protection System” by James

E. Pavlosky and Leslie G. St. Leger, 1974

2/3/2011

AAE 450

Spring 2011

Kim Madden

•Structures and Thermal Control

•Exploration Rover

•Rescue Rover

This week:

•Pressure Vessel Analysis for Exploration Rover

•Radiation Shielding for Exploration Rover

2/3/2011

AAE 450

Spring 2011

Exploration Rover – Pressure Vessel

100.00

110.00

120.00

130.00

140.00

150.00

160.00

0 1 2 3 4 5 6 7 8Ma

ss

of

Pre

ss

ure

Ve

ss

el (k

g)

Exploration Length (Days)

Mass of Exploration Rover Pressure Vessel

Al 2090-T83

Al 7075-T6

Al 2014-T6

•Only ~40 kg different between heaviest and lightest

•Other structural components will need to be analyzed

before choosing final material

2/3/2011

AAE 450

Spring 2011

Exploration Rover – Radiation Shielding

•For light shielding: ~10 g/cm2

Days 1 2 3 4 5 6 7

SA (m2) 44.0 44.3 44.6 44.8 45.1 45.1 45.6

Mass (kg) 439.9 442.6 445.5 448.2 451.1 450.9 456.5

Recommendation:

•Design for 3 or 6

days

Future Work:

•Windows/Wind shields

•Support Beams

•Flooring

2/3/2011

Week 4 Thursday (2/3) · Ares V C&C Launch Vehicle Spring 2011 ARES V C&C LAUNCH VEHICLE – SPECS...

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