AAE 450

Spring 2011

Week 6 – Thursday (2/17)

Courtney McManus

1

AAE 450

Spring 2011

Today’s Schedule

Group Roll Call

CDR

Some estimates

Section 1 Presents

Dr. Longuski shall impart wisdom upon us

Group break-out/prepare for CDR

C. McManus Project Manager 2/17/2011 2

AAE 450

Spring 2011

CDR is next week!!

Thursday (2/24) 6-8pm ARMS 1109

One vehicle representative will present:

Most aspects of vehicle should be decided

Detailed sketch

Mass/Power/Volume of vehicle and most

subsystems

PM/APM will present overall mission

timeline and configuration

2/17/2011 McManus, Courtney Project Manager 3

AAE 450

Spring 2011

Current Duration Estimates

STV Transfer: 5 yrs

CTV Transfer: 1.5 yrs

Crew Stay Time: 2 yrs

CTV Return: 1.5 yrs

Comm Sats to Halo: 1.8 yrs

Relay Sat to position:

ISPP Production: 3.2 yrs

2/17/2011 McManus, Courtney Project Manager 4

AAE 450

Spring 2011

Launch Estimates

# of Launches for STV: 9 Ares V

# of Launches for CTV: 7 Ares V

16 Ares V + 1 Earth trailing sat + 1 Crew

Total number of launches: 18 launches

Volume is biggest constraint

2/17/2011 McManus, Courtney Project Manager 5

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

2/17/2011 6

AAE 450

Spring 2011 Alexander Roth

AAE 450: Week 6 Presentations

Technical Groups:

Aerodynamics

CAD

Vehicle Groups:

CTV

Crew Capsule

Crew Launch Vehicle

Cargo Launch Vehicle

Roth, Alexander Aerodynamics & CAD

Tasks Accomplished:

Sized the Crew Capsule’s Heat Shield

2/17/2011 7

AAE 450

Spring 2011

Crew Capsule Heat Shield

Capsule very similar to Orion

Massno heat shield = 5317.78 kg

Nose Radius = 6.476 m

Max Diameter = 5.5 m

Cone Angle = 20°

L/D = 0.4

Snose = 23.76 m2

Roth, Alexander Aerodynamics & CAD

(1) Aerocapture

Maneuver

(at altitude h)

(2) Periapse

Raise Maneuver

(LEO - Final Orbit)

2/17/2011 8

AAE 450

Spring 2011

Crew Capsule Heat Shield

Roth, Alexander Aerodynamics & CAD

Avocoat-5026-39 Phenolic Impregnated

Carbon Ablator (PICA-15)

Density (kg/m3) 512.6 228

Aerothermal Performance

Limits

700 W/cm2

1 atm

2000 W/cm2

0.75 atm

Failure Mode Char spall Char spall

Heating Rate (W/cm2) < 500 < 1200

Re-entry Velocity (km/s) 10.7 12.9

Tmax (K) 3000 3000

TPS Thickness (m) 0.1524 0.0582

TPS Mass (kg) 1853.137 315.29

Combined Capsule Mass

(kg) 7170.917 5633.07

2/17/2011 9

AAE 450

Spring 2011 Austin Hasse

AAE 450: 3rd Presentation

2/ 17/ 2011

Job Description

• Aerodynamics Group Leader

• CTV Group Member

• Crew Capsule Group Member

Tasks

• Tether Sizing for Ballute

• Ballute Tank Sizing and Configuration

Hasse, Austin Aerodynamics 2/17/2011 10

AAE 450

Spring 2011

Ballute Tethers

PBO (Zylon) Material

• ρ = 1340 kg/m^3

• Tensile Stress = 5.9E9 Pa

Tether M/V

• Length = 190 m

• Mass = 306.1 kg (0.306 T)

• Volume = 0.2041 m^3

Hasse, Austin Aerodynamics

Tether Design Sketch

2/17/2011 11

AAE 450

Spring 2011

Helium Tank Design

Hasse, Austin Aerodynamics

Tank Properties

Mass (tank and Helium) =

551.757 kg (0.552 T)

Volume = 0.2079 m^3

Catia Model Ballute Storage

Crew Air Lock

Ballute Containment

Helium Tank

2/17/2011 12

AAE 450

Spring 2011

Schafer, David ADCS

AAE 450: Week 6 Presentations

Vehicle Groups:

- Communication Satellites

- Rovers

Tasks Completed:

- Small Forces at Ceres study

- Satellite Maneuver study

- CMG Saturation avoidance

AAE 450

Spring 2011

Schafer, David ADCS 2/17/2011

Space Environmental Forces and

Torques (Halo Satellites) Environmental Forces

combine to 0.00468 N

Maximum environmental torque (with current configuration) becomes 0.135 Nm

Earth-Relay maneuver needs turn of 21°

Torque of 0.135 Nm and spin-up/down of 4.5 minutes gives 1.45 hour (87 minute) transfer time

Have 1.8 hour (108 minute) window

14

AAE 450

Spring 2011

Schafer, David ADCS 2/17/2011

4 separate 4-axis

components

Total mass decreased

to 64 kg maximum

Total volume

decreased to 0.5 m3.

Power remains the

same (0.6 kW)

Control Moment Gyroscope

Future work:

•Find small forces at Relay

Satellite

•Create CMG for Relay Satellite

•Finalize CMG for Halo Satellites

•Size ADCS thrusters and

propellant of Rescue Rover

15

AAE 450

Spring 2011 Paul Frakes

AAE 450: Week 6 Presentations

Tasks Accomplished:

Non-gravitational, environmental space

torques and forces on STV

Crew Capsule: passive attitude control

Need to address configuration details

Frakes, Paul Attitude Determination and Control Systems 2/17/2011 16

AAE 450

Spring 2011

Effects considered:

solar radiation (interplanetary)

solar wind (interplanetary)

Van Allen belt particle collisions

atmospheric drag

Assume:

Cd=1, Distance between CoP and CoM = 10 m

Propellant mass required: 1011.7 kg

Collaboration with Propulsion Group required to

determine system mass

STV Environmental Torques / Forces

Frakes, Paul Attitude Determination and Control Systems 2/17/2011 17

AAE 450

Spring 2011

Only active attitude control required: initial docking Close proximity operations

defined as within 1 km*

Assume Isp = 220 s

Propellant mass required: 177.35 kg

Other maneuvers performed by ―swivel arms‖ Collaboration with Structures

Group will be required

Crew Capsule Configuration

Frakes, Paul Attitude Determination and Control Systems

*Carrico, T., et al. Proximity Operations for Space Situational Awareness

2/17/2011 18

AAE 450

Spring 2011 Sarah Jo DeFini

AAE 450: Week 6 Presentations Tasks Accomplished:

Researched Tracking, Telemetry, and

Command (TT&C) Subsystems

Rough power requirements for Supply

Transfer Vehicle Comm System

Vehicle Groups

Supply Transfer Vehicle

Supply Launch Vehicle

Communication Satellites

DeFini, Sarah Jo Communications 2/17/2011 19

AAE 450

Spring 2011

Provide data dump capabilities for all cargo

flights every one month (COMM-003)

Maximum range: 563,326,349 km From Sonia Teran

Monitor, record, and send at least 18 health &

status signals

(Receive corrective commands)

STV Comm Requirements

DeFini, Sarah Jo Communications 2/17/2011 20

AAE 450

Spring 2011

Single 1 m diameter dish

Transmit to Deep Space Network

Pointing requirement: within 2 degrees of target

Energy = 8.5 kW for 1 hour once a month for 42 months = 357 kWh

Mass = 18 kg

Volume = Negligible

STV Comm Recommendation

DeFini, Sarah Jo Communications 2/17/2011 21

AAE 450

Spring 2011

See you downstairs at 10:30!!

AAE 450

Spring 2011

Signorino, Trieste Mission Design

AAE 450: Week 6 Presentations

Vehicle Groups:

- CTV Launch Vehicles (Lead)

- CTV Transfer Vehicle

AAE 450

Spring 2011

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

• Isp = 5000s for Low Thrust and Isp = 971s for Kick

• ∆V at Earth occurs at last perigee before escape

• Geocentric Spiral • m0_leo = 350 T

• mprop_LT = 51.20 T

• Time in spiral = 2 years

CTV Spiral and Transfer to Ceres

Signorino, Trieste Mission Design 24

-10 -9 -8 -7 -6 -5 -4 -3 -2 -1 0

x 105

-4

-3

-2

-1

0

1

2

3

4

x 105

X Position (km)

Y P

ositio

n (

km

)

Geocentric Spiral for CTV - Trieste Signorino

-3 -2 -1 0 1 2 3

-2.5

-2

-1.5

-1

-0.5

0

0.5

1

1.5

2

2.5

Distance (AU)

Dis

tance (

AU

)

CTV Transfer - Trieste Signorino

Earth Orbit

Ceres Orbit

Transfer Orbit

2/17/2011

AAE 450

Spring 2011

Signorino, Trieste Mission Design 25

CTV Transfer to Ceres

Future Work:

• Investigate better rendezvous locations to minimize human flight time.

• Update ∆V information as dry mass of CTV becomes finalized

TOF

(yrs)

∆Vc

(km/s)

∆Ve

(km/s)

∆Vtotal

(km/s)

Mprop_LT

(T)

Mprop_kick

(T)

Mass to LCO

(T)

1.215 3.181 4.464 7.645 13.470 164.92 120.41

1.231 3.289 3.685 6.975 14.095 155.16 129.54

1.246 3.964 1.930 5.893 20.285 137.89 140.62

1.307 3.547 1.804 5.352 19.909 128.47 150.42

1.394 2.903 1.809 4.713 21.832 116.65 160.32

1.487 2.437 1.693 4.130 25.278 105.16 168.36

2/17/2011

AAE 450

Spring 2011

Tasks Accomplished:

Return from Ceres Trajectory

Responsibilities:

Mission Design - Member

Supply Launch Vehicle Group– Group Lead

Rover Group – Member

Ascent/Re-entry Group – Member

Sanders, Megan Mission Design

AAE 450

Spring 2011

Sanders, Megan Mission Design

Technical Details •Constrained to using motors selected by CTV

group for trip to Ceres

•Optimizing for flight time and arrival speed

•Max flight time of 1.5 years

•Arrival speed of 7.7-10 km/s

ISP Thrust

Kick Motor 971 -

Low Thrust 5000 40

2/17/2011 27

AAE 450

Spring 2011

Departure Mass: 280 tons

Return speed at LEO: 7.96 km/s

Arrival Mass: 145.8 tons

Flight Time: .91 years

Propellant Mass:

Kick Motor: 106.4 tons

Low Thrust: 27.8 tons

Mass Ratios

Kick Motor: .62

Low Thrust: .84

Results

Mission Design Sanders, Megan 2/17/2011 28

AAE 450

Spring 2011 Drew Crenwelge 17 February 2011

Power Group: Nuclear Reactor Sizing Selection

Radiator Sizing

Crenwelge, Drew Power Group 29 2/17/2011

AAE 450

Spring 2011

Nuclear Reactor Selection

30 Crenwelge, Drew Power Group

Power

(kWe)

Total

Mass

(kg)

PMAD Heat

Reject

Power

Conv.

HSHX Shield

(LiH/W)

Reactor Specific

Power

(kg/kWe)

100 4115 823 781.8 781.8 205.8 864.2 617.25 41.15

2000 53452 10690 10155 10155 2673 11225 8017 26.73

100

kWe

2000

kWe

Diameter

(m)

.747 2.26

Height

(m)

.69 1.8

Volume

(m3)

.28 2.64

2/17/2011

AAE 450

Spring 2011

Nuclear Radiator Sizing

Crenwelge, Drew Power Group 31

Total Area = 3084 m^2

Base (m) Length (m)

12 32.125

13 29.65

14 27.54

15 25.7

•Means of Deployment:

•Retractable Vs. Foldable

•Future Work:

•PMAD, HSHX Volumes

2/17/2011

AAE 450

Spring 2011 Elle Stephan 17 February 2011

Communications Satellite Vehicle Lead ISPP Harvester Design

Stephan, Elle Power 32 2/17/2011

AAE 450

Spring 2011

Ceres Orbiting Satellites

Stephan, Elle Power 33

Mass [kg]

Power

Generated

[kW]

Volume

[m^3]

Solar Array 1129 85.5 13.44

Folds in a fan-like manner for storage

Circular configuration when fully deployed

* Per satellite

2/17/2011

AAE 450

Spring 2011

ISPP Harvesters

Stephan, Elle Power

34

Mass [T] Power

[kW]

Volume

[m^3]

Regolith 15

79.6 8.2 Structure/

Equipment 1

2 harvesters per station (3 for redundancy)

collecting 15T twice a day

Minimum power required for 5 yr duration

* Per harvester

2/17/2011

AAE 450

Spring 2011

Resume at 11:05

AAE 450

Spring 2011

Dietrich, Jared N Propulsion

AAE 450

Spring 2011

Mission begins at LEO (350km),

circular spiral to Earth escape,

then Helio spiral to Ceres.

Maximum 5 year Transit time

Dry Mass at Ceres ~ 250T*

Earth Orbit must be escaped – required

a minimum of ~60N of Thrust.

90 N Thrust requirement to reach Ceres.

Best option: Magnetoplasmadynamic

Thruster (MPDT). TRL <= 3.0

*100T cushion added to STV calculated dry mass (Backup Slide 6)

37 Dietrich, Jared N Propulsion

LEO to CERES via STV

Time of Flight 3.87 years

Initial Wet mass 875 T

Dry Mass at Ceres 236 T

Kick Motor Propellant 462.2 T

Low Thrust Propellant 164.1 T

Thrust 90 N

Isp – Low Thrust 5000 sec

Isp – Kick Motor 971 sec

2/17/2011

AAE 450

Spring 2011

38 Dietrich, Jared N Propulsion

Total Estimated Power = 4.415 MW.

MPDT @ 1.5 MW each, total Power = 5.13MW

Work with power group

to determine to power

supply and masses.

Work with Attitude and

Control to determine

Propellant requirements

Power Required – LEO to CERES

Mission Required Power 5.13 MW

No. of MPDT Engines 4

Total Engine Mass 4 T4

New Total Wet Mass 879 T

New Dry Mass at Ceres 240 T

2/17/2011

AAE 450

Spring 2011 David Wyant

Feb. 17, 2011 Technical Group: Propulsion

Vehicle Groups: Rovers

Crew Ascent Vehicle

Rover Propellant Requirements and Rover

Dynamics

Wyant, David Propulsion 2/17/2011 39

AAE 450

Spring 2011

Results

Wyant, David Propulsion

Rescue Rover Exploration Rover

Consumption

(per trip)

Tank

Volume

(m3)

Tank

Mass

(kg)

Consumption

(per day)

Tank

Volume

(m3)

Tank

Mass

(kg)

H2 157.03 kg 2.307 29.34 4.24 kg .4482 5.54

O2 785.14 kg 0.7088 5.154 33.93 kg .2144 1.559

Rescue Rover

Total consumption

based on uses

Exploration Rover

For 2 years

○ 6.19 tons H2

○ 49.52 tons O2

2/17/2011 40

AAE 450

Spring 2011

We will in fact

be airborne,

however not

enough to float

away

Time of Flight

3 – 22 sec

Rover Dynamics

Wyant, David Propulsion 2/17/2011 41

AAE 450

Spring 2011 Michael Hill

AAE 450: Presentation 3 Team Tasks:

Propulsion Group Leader

CTV Propulsion

Hill, Michael Propulsion 42 2/17/2011

AAE 450

Spring 2011

Selection of Low-Thrust Engine

Decision radically changed after

Heliocentric Spiral was introduced

Will use 4 High Thrust MPD Thrusters

Isp = 5000 sec @ 10 N

Mass/Thruster (Includes Power Processing

Unit) = 664 kg

Total Mass of Thrusters = 2656 kg[1]

Total Power Required = 1.96 MW

43 Hill, Michael Propulsion 2/17/2011

AAE 450

Spring 2011

Spin-up/Attitude Engines

Will use MMH/N2O4 engines (carry whole

trip).

30 N @ Isp = 328 sec

44 Hill, Michael Propulsion

Spin-up Propellant mass 1024 kg

Attitude Control propellant mass[2] 392 kg

- MMH mass 422 kg

- MMH Tank Volume[3] 0.533 m3

- N2O4 mass 994 kg

- N2O4 Tank Volume[3] 0.765 m3

Thrusters mass[4] 558 kg

2/17/2011

AAE 450

Spring 2011

Zachary Richardson Week 6 Presentation: 2/17/2011

Group Lead: Human Factors & Science

- ISPP Oven Sizing and Configuration

- ISPP Electrolysis and Production

Tasks Accomplished:

Researched Oven mass/power/volume and heat loss

Developed concepts for Ceres ISPP production

Updated ISPP production values to fit mission timeline

Researched Electrolysis theory and power requirements

Richardson, Zachary Human Factors & Science 2/17/2011 45

AAE 450

Spring 2011

ISPP Oven Design “Kiln”

Richardson, Zachary Human Factors & Science

Single Oven*

Regolith contained

(kg)

30000

Temperature

Difference (K)

306

Inside Volume (m3) 15

Outside Volume (m3) 32.85

Mass of oven (kg) 2951

Power Required (kW)

*including insulation

(PSE)

~25

V(in) = 15 m^3

Entrance Chute

Exit Chute

By: Zachary

Richardson

To collection unit and

conveyor belt *Can be scaled for larger internal volumes

2/17/2011 46

AAE 450

Spring 2011

Upcoming Tasks Resize Oven for 24 hour heating process

Determine mass for complete electrolysis system

Determine ISPP facility schematics

Production and Electrolysis

Richardson, Zachary Human Factors & Science

ISPP Production: 3.2 years *With CTV and Rover #’s from 2/16

Water extracted (kg) 29461

Oxygen extracted (kg) 53317

Hydrogen extracted

(kg)

165185

Electrolysis Power

(kW)

330

Production based on requirements for the following: Kick motor, low

thrust, CTV Ceres transport

Rovers

Human Factors

Electrolysis Efficiency = 80% (projected)

2/17/2011 47

AAE 450

Spring 2011

Resume at 11:45

AAE 450

Spring 2011 Ben Stirgwolt AAE 450: Week 6 Presentations

Human Factors & Science:

Exploration Rover — Layout & Instrumentation

Food & Hydroponics, revisited

Stirgwolt, Ben Human Factors & Science 49 2/17/2011

AAE 450

Spring 2011

Stirgwolt, Ben Human Factors & Science

Exploration Rover

50

Science Instruments:

Mass: 356.7 kg

Volume: 1.3 m3

Power: 0.7 kW

HF&S Totals:

Mass: 3028 kg

Volume: 61.4 m3

Power: 6.9 kW

2/17/2011

AAE 450

Spring 2011

Food & Hydroponics

Stirgwolt, Ben Human Factors & Science 51

Key Numbers

STV Food:

Mass: 10620 kg

Volume: 84 m3

CTV Food:

Mass: 2605 kg

Volume: 21 m3

CTV Hydroponics:

Mass: 5790 kg

Volume: 20 m3

2/17/2011

AAE 450

Spring 2011

Andrew Curtiss Groups

- Structures & Thermal

- Earth Ascent, Reentry

- Supply Transfer Vehicle

- Supply Launch Vehicle

Accomplishments

- STV Design/Configuration

- Launch Vehicle Estimations

- Crew Capsule Heat Shielding Research

- Crew Capsule Swivel Arm Design

- STV Magnetic Module Connector Design

2/17/2011 52

AAE 450

Spring 2011

r

Magnetic Module Connector (MMC)

- Electromagnets used to connect

modules of STV

- No moving parts

- No spacewalks required to

assemble STV in orbit

- Power supplied from center module

- Highest power required during kick

motor burn when low thrust motors

are off

- Easy to jettison outer modules upon arrival at Ceres

- MMC’s iron bar cores serve as conductors to supply outer

modules with power for low thrust motors

- Easy to change basic design parameters in MATLAB script

2/17/2011 53

AAE 450

Spring 2011

Assumptions:

- 2 Center Modules

- 6 Outer Modules on each Center Module

- 2 MMC’s connecting each Outer Module

- Kick Motor Thrust = 350,000 N

- Average Outer Module Mass = 25,000 kg

- Kick Motor Propellant Mass = 200,000 kg

- 12 Volt Power Supply

Total Mass (24 MMC’s) = 1311.3 kg

Total Power Requirement (At Peak Acceleration) = 1.248 kW

2/17/2011 54

AAE 450

Spring 2011

Kim Madden - Structures & Thermal Control

- Exploration and Rescue Rover

- Group Lead

This week:

-Revised Pressure Vessel -Took into account larger inside volume

-Flooring -Flat surfaces to work on, storage space under

-Windshields/Windows -Front and Back to have ample visibility

2/17/2011 55

AAE 450

Spring 2011

Circular Cross Section of Rover

1.5 m

2.8 m Outside: Al, 2cm thick

-Doubles as radiation

shielding, pressure vessel,

and resists buckling

Polyethylene ,4cm –

Radiation shielding

Floor: Al, 2 cm thick

-Can hold 2/3 of HFS

mass during launch

Assumptions:

-Accel at launch ~6g’s

4.3 m

4.0 m

2/17/2011 56

AAE 450

Spring 2011

Windshields/Windows Shape Hemisphere 2:1 Ellipsoid

Mass (for 2), kg 1398.7 723.9

Structural Volume

(for 2), m^3 1.16 0.60

Internal Volume

(for 2), m^3

41.8

20.9

a

a

½a

a Assumptions:

-Made of Polycarbonate

-Weld Efficiency = 70%

Total Structural Mass: 7.01 tons

Total Structural Volume: 4.25 m^3

Total Volume (structural + internal): 85.03 m^3 2/17/2011 57