Week 11 Thursday (3/24) - Purdue University College of ... · Week 11 – Thursday (3/24) Courtney...

AAE 450

Spring 2011

Week 11 – Thursday (3/24)

Courtney McManus

3/24/2011

AAE 450

Spring 2011

Schedule for the day

Project Vision ideas!

Presentations!

Lecture!

3/24/2011

AAE 450

Spring 2011

Project Vision

Emblem

T-shirt, vest, etc ideas

Would anyone like to be point person for

this?

3/24/2011 McManus, Courtney Project Manager

AAE 450

Spring 2011

3/24/2011

Section 1 Presentation Schedule

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 for 1 hour (change rooms)

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 Wyantt 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 Alexander Roth

AAE 450: Week 10 Presentations Technical Groups:

Aerodynamics

CAD

Vehicle Groups:

CTV

Crew Capsule

Crew Launch Vehicle

Cargo Launch Vehicle

Roth, Alexander Aerodynamics & CAD

Tasks Accomplished:

Fitting all the CTV’s components into Ares V

payload shrouds

Pictorial overview of the CTV’s configuration

throughout the mission DISCLAIMER FOR ALL SLIDES:

CAD Models Combined Together by Alexander Roth

Individual CAD Models Created by: Trieste Signorino, Brendon White, Drew

Crenwelge, Austin Hasse, Michael Hill, Jared Dietrich, & Megan Sanders.

AAE 450

Spring 2011


Total Launches for CTV = 7

1 for Chassis and Crew Cabin 3 for Secondary Tanks

3 for Primary Tanks

Step 1: Launching CTV

AAE 450

Spring 2011


Step 1: Launching CTV

CAD Models Combined

Together by Alexander Roth

Individual CAD Models Created

by: Trieste Signorino, Brendon

White, Drew Crenwelge, Austin

Hasse, Michael Hill, Jared

Dietrich, & Megan Sanders.

Chassis & Crew Cabin (1x)

Primary Tanks

[Dark Grey

Frame] (3x)

Secondary Tanks

(for Earth Departure)

[Tan Frame] (3x)

AAE 450

Spring 2011 Step 2: CTV Built in LEO


(aka: Geocentric Apogee Raise)

Final configuration with

Primary and Secondary

tanks attached every-other

CAD Models Combined







P

P P

P

P

S S

S

S

S

AAE 450

Spring 2011 Step 3: Crew Arrival


CAD Models Combined







Crew Cabin lowers slightly

so Capsule can dock

unrestricted

Capsule Docks to side of

Crew Cabin (only

temporarily) to transfer

astronauts

AAE 450

Spring 2011 Step 3: Crew Arrival


CAD Models Combined







Capsule then

moves

autonomously

to top of CTV

for parking

Capsule

remains there

until earth

aerocapture

and reentry

AAE 450

Spring 2011 Step 4: Earth Departure


Empty Secondary

tanks are then

detached and

discarded

All propellant in Secondary tanks

is used on a burn

AAE 450

Spring 2011 Step 5: Artificial Gravity to Ceres


CAD Models Combined Together

by Alexander Roth

Individual CAD Models Created by:

Trieste Signorino, Brendon White,

Drew Crenwelge, Austin Hasse,

Michael Hill, Jared Dietrich, &

Megan Sanders.

Tether fully extended to 84.98m (1 kwan)

Crew Cabin rotates about the tanks (which

act as a center counter weight)

Radiator panels opened to

cool reactor

AAE 450

Spring 2011 Step 6: Ceres Orbit Insertion


CAD Models Combined







Tether retracted

back for engine

burns (crew

cabin hooks

back into rails

for stability)

Radiator panels

closed and

folded for

engine burns

AAE 450

Spring 2011 Step 7: Ceres Descent & Hover


CAD Models Combined







Hovering on Ceres requires

only the small pink ―Ceres

Regime‖ motors

Size difference

compared to ―Kick‖

motors shown below

AAE 450

Spring 2011 Step 8: Artificial Gravity from Ceres


CAD Models Combined







Same configuration as in Step 5, except

the CTV is traveling back to Earth

AAE 450

Spring 2011 Step 9: Earth Aerocapture


CAD Models Combined







CTV configuration as it

approaches Earth

Capsule releases (shown

next slide)

CTV deploys ballute for

aerocapture at Earth (but

stays in LEO)

AAE 450

Spring 2011 Step 10: End of Life (Capsule)


CAD Models Combined







Capsule reenters atmosphere and splashes down

back on Earth

Crew returns back home after long Ceres mission

AAE 450

Spring 2011 Step 10: End of Life (CTV)


CTV stays in LEO

Maintains ability to be reused

AAE 450

Spring 2011 Close-ups of Smaller Items Attached

to the CTV


MPD’s attached to

tethers, and can move

freely along them

Capsule docking port for

parking

Tether spindle for Crew

Cabin

Reactor mounting

bracket near the

Capsule parking area

AAE 450

Spring 2011 Close-ups of Smaller Items Attached

to the CTV


Large Telescope (for

receiving) mounted on top of

the Attic

Small Telescope (for

transmitting) mounted on top

of the Attic

Phased Array mounted on

the top mount near the

Capsule parking spot

AAE 450

Spring 2011 Austin Hasse

AAE 450: Final Presentation

3/ 24 / 2011

Job Description

• Aerodynamics Group Leader

• CTV Group Member

• Crew Capsule Group Member

Tasks

• Final Designs of Damocles Ballute, ARC Ballute, and ARC Re-entry Parachute

• CATIA Models for Damocles Ballute, ARC Ballute, and ARC Re-entry Parachute

Hasse, Austin Aerodynamics 3/24/2011

AAE 450

Spring 2011

Damocles Aerocapture Ballute

Hasse, Austin Aerodynamics

Damocles Ballute CATIA model by Austin Hasse

Damocles Vehicle Courtesy of Alex Roth

3/24/2011

AAE 450

Spring 2011

Damocles Ballute Specifications

Ballute Spec. Value

Ballute Mass 2.809 T

Ballute Packed Volume 1.97 m^3

Ballute Tank Mass

Ballute Tank Volume

2.806 T

1.05 m^3

Tether Mass 3.516 T

Tether Volume 0.25 m^3


Total Damocles Ballute System Value

Mass 9.131 T

Volume 3.27 m^3

3/24/2011

AAE 450

Spring 2011

ARC Aerocapture Ballute


ARC Ballute CATIA model by Austin Hasse

ARC Vehicle Courtesy of Alex Roth

3/24/2011

AAE 450

Spring 2011

ARC Ballute Specifications

Ballute Spec. Value

Ballute Mass 179.53 kg

Ballute Volume 0.1274 m^3

Ballute Tank Mass 13.55 kg

Ballute Tank Volume 0.0051 m^3

Tether Mass 79.49 kg

Tether Volume 0.073 m^3


Total ARC Ballute System Value

Mass 272.57

Volume 0.2055 m^3

3/24/2011

AAE 450

Spring 2011

Parachute Design


ARC Parachute CATIA model by Austin Hasse

ARC Vehicle Courtesy of Alex Roth

Parachute Spec. Value

Parachute Radius 15.78 m

Packed Volume (3) 0.47 m

^3

Mass (3) 0.54 T

3/24/2011

AAE 450

Spring 2011

Schafer, David ADCS

AAE 450: Week 11 Presentations

Vehicle Groups:

- Communication Satellites

- Rovers

Tasks Completed:

- STV inertia coding

- Relay satellite saturation

avoidance

AAE 450

Spring 2011

Schafer, David ADCS 3/24/2011

Halo Satellites Ecco 1 and 2

Force [N] Torque

[Nm]

Mass [kg] Power

[kW]

Volume

[m3]

Environmental

forces

0.005 0 0 0 0

Environmental

Torques

0 0.135 0 0 0

Positioning

system

0 0 660 0.06 1.275

CMG system 0 1.2 20 0.8 0.0062

Propulsion

system

NA 0 10.9 0 0.8

Propellant 0 0 1250 0 0.128

AAE 450

Spring 2011

Ecco 1 and 2 Saturation

Satellite passes out of phase every 4.5 hours

Takes under 2.7 hours to bring CMG’s back to 0% saturation

Done while satellite is out of phase with mission crew

Controlled by computer logic

Perturbs a single gyro to force others to counteract torque

Would cause loss in communications if done while in phase with mission crew

3/24/2011 Schafer, David ADCS

AAE 450

Spring 2011

Relay Satellite Ecco Base

Force

[N]

Torque

[Nm]

Mass [kg] Power

[kW]

Volume

[m3]

Environmental

forces

0.0014 0 0 0 0

Environmental

Torques

0 0.02 0 0 0

Positioning

system

0 0 660 0.06 1.275

CMG system 0 0.12 4.5 0.08 0.0016

Reaction

Wheel system

0 0.5 20 0.3 0.0336

Propulsion

system

NA 0 10 0 1

Propellant 0 0 45 0 0.123


AAE 450

Spring 2011

Ecco Base Saturation

Dual attitude control system

CMG’s operate alone until near saturation

Computer logic perturbs a gyro as the rest of the

gyros torque through their saturation point

Perturbed gyro forces gyros to torque against each

other and pull CMG system out of saturation

Reaction wheels pick up control of full system

Correct for satellite perturbations from outside and

inside (CMG) torques

Reaction wheels shut down after saturation

avoided


AAE 450

Spring 2011

Schafer, David ADCS 3/24/2011

Position/attitude found

using Motion Reference

Units

Inertial measurements

catalogued with dual

computer system

4 separate gimbaled 2.5

kN thrusters (2 DOF)

Requires around 100 kg of

propellant for full roundtrip

(attitude control only)

Rescue Rover Control

ADCS thrusters

AAE 450

Spring 2011 Paul Frakes


ADCS for STVs (Cassiopeia and Cepheus)

and crew capsule (ARC)

Environmental space forces and torques on

STVs and ARC

Solar radiation, solar wind, Van Allen belt particle

collision, gravity gradient, atmospheric drag

Steering law for STVs

Comm. dish pointing on STVs

ARC docking and additional maneuvers

Frakes, Paul Attitude Control (ADCS) 3/24/2011

AAE 450

Spring 2011

STV Attitude Determination and Control

Determination: Motion Reference Unit

(inertial) and computer system

Control: 6 motors per vehicle, gimbaled on

Canfield joints

Correct for:

Misalignment/offset during Earth kick

Environmental forces and torques: Van Allen belt

particle collisions, atmospheric drag, solar

radiation, solar wind, gravity gradient

Steering law

Frakes, Paul Attitude Determination and Control Systems 3/24/2011

AAE 450

Spring 2011

Notes: Thrust in the direction of velocity

Each STV represented by

model as shown right (with 6

strap-on shrouds, not 4)

ACS thrusters coupled on 3 shrouds

No spin (3-axis stabilization)

ADCS mass required:

STV1: 2342 kg

STV2: 2573 kg

STV Attitude Control

Frakes, Paul Attitude Determination and Control Systems

Graphic courtesy Jared Dietrich

3/24/2011

AAE 450

Spring 2011

Propose using Canfield joint for

both vehicles

3 DoF system enabling full

hemispherical pointing

TRL ~4

Proposed by NASA for Reaction

Control System on Orion Crew

Capsule

Reduces number of required RCS

thrusters on capsule

Using one type of gimbal reduces

overall system complexity,

development cost

STV Comm. Dish Pointing /

Crew Capsule RCS


AAE 450

Spring 2011

Crew Capsule Maneuvers

Initial docking

Drop into slightly lower LEO orbit to chase CTV,

raise orbit to dock

Four (4) near-CTV maneuvers

Before Earth departure to make CTV nearly

axisymmetric

Upon Ceres arrival for rock storage access

Before Ceres departure (again for symmetry)

Upon Earth arrival to pick up crew

Separation from CTV for Earth entry


AAE 450

Spring 2011

Crew Capsule Maneuvers – Near-CTV

Frakes, Paul Attitude Determination and Control Systems

1. Before Earth departure

to make CTV nearly

axisymmetric

2. Upon Ceres arrival for

rock storage access

3. Before Ceres departure

(again for symmetry)

4. Upon Earth arrival to

pick up crew

1, 3 2, 4

CAD model courtesy Alex Roth

3/24/2011

AAE 450

Spring 2011 Sarah Jo DeFini


Vehicle Groups:

Supply Transfer Vehicle

ISPP Stations

This week’s focus:

Final Design Presentation Summaries

DeFini, Sarah Jo Communication 3/24/2011

AAE 450

Spring 2011

Monitors, records, and sends up to 24 health and status signals

Transmits to TDRSS (15 m dish) once a month

Maximum transmitting distance: 563,300,000 km

Pointing requirement:

within 2 degrees of target

Operating Frequency:

26.5 GHz (S-band)

Data Collection Rate: 368 bps

Antenna efficiency: 0.7

STV Communications

DeFini, Sarah Jo Communications

Cassiopeia and Cepheus

Tracking, Telemetry, and Command

Earth

Ceres

Drawing not to scale (Sarah Jo DeFini)

3/24/2011

AAE 450

Spring 2011

STV Comm Mass, Power, Volume

Telemetry Dish

Mass = 1.7 kg

Energy = 8.5 kW for 1 hour once a month for 17 months = 145 kWh

18 months = 153 kWh

Volume = 0.005 m^3

General Processing Computer

Mass = 29 kg

Power = 0.55 kW

Volume = 0.025 m^3

DeFini, Sarah Jo Communications 3/24/2011

AAE 450

Spring 2011

o Station-Satellite

• RF dish (1 m diameter)

• Route through CTV when

available

o Station-Tanks

• RF Dish (10 cm diameter)

o Station-Harvester:

• Wireless Communication

• Coverage Area ~150 m

ISPP Station Communications

DeFini, Sarah Jo Communication

ISPP Station

Harvester

Harvester

Storage

Tanks

APES 1&2

Telemetry and Low-Quality Visual

Drawing not to scale (Sarah Jo DeFini)

3/24/2011

AAE 450

Spring 2011

RF Dish – Tanks

Mass: 0.18 kg

Power: 5 W

Volume: 0.05 m^3

(folded)

RF Dish – Station

Mass: 0.42 kg

Power: 1.6 kW

Volume: <0.05 m^3

(folded)

Wireless Antennas

Mass: 0.034 kg each

○ 1 ISPP + 3 harvesters =

0.14 kg

Power: 0.1 W each


0.4 W

Volume: 0.00004 m^3

each


0.0002 m^3

ISPP Comm Mass, Power, Volume

DeFini, Sarah Jo Communication 3/24/2011

AAE 450

Spring 2011

See you downstairs at 10:30!!

3/24/2011

AAE 450

Spring 2011

Signorino, Trieste Mission Design


Vehicle Groups:

- CTV Launch Vehicles (Lead)

- CTV Transfer Vehicle

AAE 450

Spring 2011

CTV Launch Vehicles

Launch 1: CTV Payload Ares V (1)

○ Mass = 131,033 kg

○ Volume = 412 m3

Launch 2-4: Primary Tanks Ares V (3)

○ Mass = 144,605.17 kg

○ Volume = 565.6 m3

Launch 5-7: Secondary Tanks Ares V (3)

○ Mass = 187,250 kg

○ Volume = 688 m3

Launch 8 : Crew Ares I (1)

○ Mass = 9835.93 kg

○ Volume = 33.04 m3

CTV Launch Vehicles

http://www.nasa.gov/mission_pages/constellation/ares/ares_naming.html

* Using extended shroud for Ares V

3/24/2011

AAE 450

Spring 2011

CTV Outbound Trajectory

Perform ∆V from LEO • ∆V = 4.76 km/s

• mprop = 728,716 kg

Turn on MPD Thrusters Thrust in direction of velocity vector with T = 33N

TOF is 1.4 years

mprop = 29,842 kg

Perform ∆V at Ceres to enter LCO

∆V = 2.18 km/s

mprop = 134,432.5 kg

Signorino, Trieste Mission Design 3/24/2011

AAE 450

Spring 2011

CTV Return Trajectory

Perform ∆V for Ceres Departure ∆V = 2.91 km/s

mprop = 203,000 kg

Turn on MPD Thrusters Thrust with 20N in direction of velocity

TOF = 1.25 years

mprop = 17,000 kg

V∞ = 7.89 km/s

Signorino, Trieste Mission Design 3/24/2011

AAE 450

Spring 2011

Food Ops

Since we got so far ahead this

morning….we’ll start presentations at 10:40

Get food!

Thanks, Mission Design Group!

3/24/2011

AAE 450

Spring 2011

Tasks Accomplished:

Earth Trailing Relay Satellite

Supply Launch Vehicle

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

Relay Satellite Transfer Orbit

Picture

by

Megan

Sanders

AAE 450

Spring 2011

Delta V (km/s)

Escaping Earth 16.935

Entering Transfer Trajectory 1.656

Leaving Transfer Trajectory 8.208

Total 26.799

Results

Mission Design Sanders, Megan

• 90° transfer angle

• Will end up 90° behind earth

• Will take half a year to get in place

AAE 450

Spring 2011 Drew Crenwelge 24 March 2011

Power Group: Power Budget – CTV

Radiation Shielding – CTV

Radiator Sizing -- CTV

Nuclear Reactor -- CTV

Crenwelge, Drew Power Group 3/24/2011

AAE 450

Spring 2011

CTV Power Budget

Crenwelge, Drew Power Group

Area Component Power Requirement (kW)

Crew Cabin Food system 17

Recreation 2

House Cleaning 1

Maintenance System 2

Health Care system 2

Personal Comm. Devices 1

Air Filtration/Recycling System 16

Air Circulation & Ducting 2

Communication Dish/System 11

Freezer(s) 2

Hydroponics 2

Water Regeneration System 0.23

Center Low Thrust Motors 1960

Counter Weight Alternate Control Devices (CMG's) 0.6

3/24/2011

AAE 450

Spring 2011

Radiation Shielding


LiH

W

Core

Radiation Shielding Specifications

Thickness

1st Layer of LiH 0.108 m

Tungsten Layer 0.053 m

2nd Layer of LiH 0.505 m

Mass

Lithium Hydride 1055 kg

Tungsten 2629 kg

Total 3685 kg

Lithium Hydride Neutron Shielding

Tungsten Gamma Shielding

By Drew Crenwelge

3/24/2011

AAE 450

Spring 2011

Heat Rejection - Radiators


Parameters Value

Thermal Output 8.4 MW

Solar Flux ~1400 W

Carbon-Carbon Emissivity .85

Stefan-Boltzmann Constant 5.6704e-8 W m^-2 K^-4

Coolant Temperature 890 K

Environmental Temperature 167 K

Radiator Area 278 m^2

•Carbon-Carbon Radiator Panels

•Coolant = Liquid Sodium Potassium

3/24/2011

AAE 450

Spring 2011

Nuclear Reactor – Power Source


Power

(kWe)

Total

Mass

(kg)

PMAD Heat

Reject

Power

Conv.

HSHX Shield

(LiH/W)

Reactor Specific

Power

(kg/kWe)

2100 25872 5715 3723 5942 2755 3685 4051 12.86

Width (m) 1.8

Height (m) 1.55

Volume (m3) ~5.0

By Drew Crenwelge

3/24/2011

AAE 450

Spring 2011 Elle Stephan 24 March 2011

Communications Satellite Vehicle Lead ISPP Harvester Design

Stephan, Elle Power 3/24/2011

AAE 450

Spring 2011

Ceres Orbiting Satellites

Stephan, Elle Power

Mass [kg]

Power

Generated

[kW]

Area [m²]

Solar Array 710 53.7 845

• Use of coil-able beam to

allow for compact storage

during transfer

* Per satellite

3/24/2011

AAE 450

Spring 2011

ISPP Harvesters

Stephan, Elle Power

*Based on 24hr day per harvester (4 trips per day)

Mass [kg] Power [W] Volume [m^3]

487 1579 7.83

Dimensions

Length [m] 2.75

Height [m] 1.5

Depth [m] 1.75

*Excluding rocker-bogie drive system (6 total wheels)

3/24/2011

AAE 450

Spring 2011

Reconvene at 10:55

AAE 450

Spring 2011

62 Dietrich, Jared N Propulsion

62

AAE 450

Spring 2011



KICK MOTOR

Quantity 6 (3 per STV)

Mass 7,967 kg

Power 0

Volume 73.200 m^3

Thrust 1,500 kN

Isp 458.3 sec

LO2

LH2

Ceres

Kick

4.15 m

2.14 m

Kick Kick

AAE 450

Spring 2011



LO2

LH2

Ceres

2.2 m

1.55 m

Ceres Regime Motor


Mass 181.2 kg

Power 0

Volume 0.070 m^3

Thrust 100 kN

Isp 452 sec

AAE 450

Spring 2011

Power required

determined by Thrust

and Isp.

Total Power = 2.45

MW

Total Mass = 3,984 kg

65


Dietrich, Jared N Propulsion

MPD THRUSTERS


Mass 1,992 kg

Power 1.225 MW

Volume 0.005 m^3

Thrust 25 N

Isp 5000 sec

AAE 450

Spring 2011

Configuration of each

STV:

3 MPDTs

1 Ceres Regime Motor

3 Kick Motors

1 Skirt

Mass savings after

Kick Motor jettison:

10,991 kg


STV Configuration, Kick Motor Jettison – Jared Dietrich


AAE 450

Spring 2011

Ares V:

Payload Mass = 188 T

Usable Volume = 1,410 m^3

Cost = $1,826/kg

Total Cost for STV

$1.94 Billion

Wet Mass = 1.067 MT


Supply Launch Vehicle – Jared Dietrich

Supply Launch Vehicle

AAE 450

Spring 2011 David Wyant

March 24, 2011 Technical Group: Propulsion

Vehicle Groups: Exploration Rovers

Rescue Rover

Crew Capsule

Rover Propulsion Overview

Wyant, David Propulsion 3/24/2011

AAE 450

Spring 2011

Drive Train & Suspension

Wyant, David Propulsion

Exploration Rover

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

Engine 135.02 40 0.3176

Transmissions 73.65 N/A 0.148

Chassis 1948.2 N/A 0.9093

Suspension 200.0 N/A N/A

Wheels 81.92 N/A 0.7226

Exploration Rover Stats

Dry mass: 11,502.6 kg

Power: 25.22 kW

Volume: 65.74 m3

Nominal Operating

Speed of 14.4 kmh (4

m/s)

3/24/2011

AAE 450

Spring 2011

Main engine

6 kN Thrust

10:1 Throttling Ratio

Propellant Mass: 2127.7 kg

Rescue Rover Engine Sizing

Wyant, David Propulsion

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

Main Thruster 12.15 N/A 0.1015

ADCS Thrusters 28.0 N/A 0.002

Maneuvering

Motors 2.88 4.66 .0608

Maneuvering Motors

Wheels to maneuver

for airlock docking

Nominal Speed of 7.2

kmh (2 m/s)

3/24/2011

AAE 450

Spring 2011 Michael Hill

AAE 450: Final Presentation Team Tasks:

Propulsion Group Leader

CTV Propulsion

Hill, Michael Propulsion 3/24/2011

AAE 450

Spring 2011

Kick Engine

LH2/LOX

F = 1,500 kN @ Isp = 458.30 sec

T/W = 57.57

Hill, Michael Propulsion

System Mass (kg) / Engine

Combustion Chamber 298.21

Nozzle 344.81

Injector 400.28

Feed 649.45

Cooling 915.49

O2 Turbomachinery 42.45

H2 Turbomachinery 5.19

TOTAL: 2655.88 Michael Hill

3/24/2011

AAE 450

Spring 2011

Spin-up/Attitude Engines

Will use MMH/N2O4 engines (carry whole

trip).

30 N @ Isp = 328 sec


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

3/24/2011

AAE 450

Spring 2011

Low Thrust Engine

Magnetoplasma Dynamics (MPD) Thruster (4x)

Isp = 5000 sec @ 10 N

Power Required = 490 kW/engine (Total = 1.96MW)



Engine 51.5

Power Processing

Unit

612.5

TOTAL: 664

Michael Hill

3/24/2011

AAE 450

Spring 2011

Ceres Regime Engine (and FORCE)

Require 16.67 kN to 33.33 kN

Isp = 468.76 sec - 469.08 sec

T/W = 61.49



Combustion Chamber 9.67

Nozzle 2.50

Injector 7.57

Feed 12.28

Cooling 17.32

O2 Turbomachinery 1.27

H2 Turbomachinery 4.65

TOTAL: 55.25

Michael Hill 3/24/2011

AAE 450

Spring 2011

Zachary Richardson Week 11 Presentation: 3/23/2011

Group Lead: Human Factors & Science

- Finalized ISPP Production

- ISPP Facility Layout

Tasks Accomplished:

Finalized Electrolysis/Oven/Production rates for ISPP

Finalized ISPP schematic design and components with the fellow

ISPP group members

Updated ISPP production values to fit mission timeline

Helped ISPP group members with final tasks

Richardson, Zachary Human Factors & Science 3/24/2011

AAE 450

Spring 2011 Total ISPP production, assumptions

and origin of requirements

Richardson, Zachary Human Factors & Science

Note: Numbers are from various worst

case scenarios so these values will

most likely be reduced

Updated Total Production

Values (for 1 ISPP station)

Production Time (yrs) 2.256

Production Time

(days)

824

*Water extracted (T) 46.39

**Hydrogen extracted

(T)

118.5

**Oxygen extracted

(T)

545.6

*Stored at Ceres ambient temp (ice)

**Stored in liquid form

Production values from the following sources:

Rescue/Exp. Rovers

Return and Transfer engines

Life Support

Assumptions:

Rescue: 1 trip per week

Rovers expend 100% of water and oxygen /trip

Low Thrust and Ceres Kick are case where final V∞ arriving at Earth = 7.89 km/s

Production values include 20% fudge factor for extra supply

3/24/2011

AAE 450

Spring 2011

ISPP Facility (Mass/Power/Volume)


Specifications of Single ISPP Facility

Component Mass (T) Power

(kW)

Volume

(m^3)

Nuclear Power Plant

(w/radiators)

12.5 N/A 23.9

Oven 3.82 N/A* 43.9

Collection Bin & Conveyor

Belt System

0.12 0.4 1

Electrolysis 6.26 341 15.3

Pipes/Condensers/Pumps 0.638 70.9 1.9

Computer and

Communications

0.016 5.4 0.06

Storage Tanks ** 0.046 164 46.8

Harvesters 1.61 3.56 28.3

TOTALS: 25.01 585 161

Assumptions:

*Oven heated by

Reactor thermal

energy.

** Hydrogen and

Oxygen Tanks are

being reused from

STV

3/24/2011

AAE 450

Spring 2011

ISPP Layout


Nuclear Power Plant, Oven, and Electrolizer are placed inside core STV unit (Ares-V cargo bay)

STV Hydrogen and Oxygen tanks are reused for ISPP storage

Collection Bin and Input/Output Conveyor Belts are deployed upon arrival

Harvesters are placed in exterior STV cargo shrouds and begin regolith collection upon arrival

3/24/2011

AAE 450

Spring 2011

Reconvene at 11:20

AAE 450

Spring 2011 Ben Stirgwolt AAE 450: Final Presentation

Human Factors & Science:

Artificial Gravity

Radiation Sources & Limitations

Hydroponics

Experiments & Science Equipment

Rovers

Stirgwolt, Ben Human Factors & Science 3/24/2011

AAE 450

Spring 2011

Stirgwolt, Ben Human Factors & Science

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

3/24/2011

AAE 450

Spring 2011

Radiation Sources


Radiation Source Amount (Sieverts—SV)

Galactic Cosmic Radiation (GCR) 0.60 Sv/year

Solar Particle Event (SPE) 4.50 Sv/day

Trapped Radiation 5.00E-4 Sv/day

Manmade Sources

(i.e. radioisotropic power generators) 0.05 Sv/year

Values based on ―Spaceflight Radiation Health Program at JSC,‖ Ref. 2

Blood forming

organs Eyes Skin

Annual Exposure

Limit (Sv) 0.5 2.0 3.0

3/24/2011

AAE 450

Spring 2011


Hydroponics

Photo by: Ben Stirgwolt

• Produces 5% of daily required food

• Utilizes LEDs to keep temperature

low & low power required

• Plant transpiration dehumidified

and then recycled

• System serves as redundancy for

environmental control system

• Crop selection based on nutritional

content and variety:

• Strawberry

• Chard

• Tomato

• Green onion

• Radish

• Sweet potato

3/24/2011

AAE 450

Spring 2011


Science & Experimental

Rover Equipment & Experiments

o Heat flow probe

o Electromagnetic sounder

o Thermal emission spectrometer

o Alpha particle X-ray spectrometer

o Microscope

o Magnetic array

o Rock abrasion tool

o Panoramic cameras

o Surface Electrical properties experiment

o Seismic experiment

o Meteorite experiment

o Transverse gravimeter

o Small research telescope

o UV Astronomical telescope

Ceres Surface

Properties

Physics &

Astronomy

3/24/2011

AAE 450

Spring 2011


Rovers

• Sufficient room for crew of 2 for 7 days

o Separate areas for navigation, sleep,

experimentation

• 2 docking ports—one on either side of rover

• 2 robotic arms—fore & aft

o Move regolith into storage containers

o Rocks of interest examined on-site in

glove-box

• Capable of rescuing 4 astronauts

o 2 medical beds & stocked with

medical supplies

o Capable of mission length of 1 day

• 2 docking ports—one on either side of

rover

Exploration Rover

Rescue Rover

Sketch by Ben Stirgwolt

Cockpit of Exploration Rover

3/24/2011

AAE 450

Spring 2011


Color Schemes

Summer Day

Torchlight

Social Butterfly

Bee

Midday

Bunglehouse Blue

Loch Blue

Georgian Bay

Denim

Blue Sky

• Selection of colors for common area of CTV

• Astronauts select their individual bedroom colors

Mass: 1.42 kg

Volume: 1.18E-3 m3

Power: 0.0 kW

www.shirwin-williams.com

3/24/2011

AAE 450

Spring 2011

Andrew Curtiss Groups

- Structures & Thermal

- Crew Capsule

- Supply Transfer Vehicle

- Supply Launch Vehicle

Accomplishments

- STV Design/Configuration

- Launch Vehicle Estimations

- Crew Capsule Swivel Arm Design

- STV module connector, manifest, hydrogen tankage, radiation

shielding, thermal control system, landing gear design

- Payload storage container/STV vessel design

- Crew Capsule Capsule structural mass estimation, heat shield

backing structure estimation

3/24/2011

AAE 450

Spring 2011

STV Landing Legs

Design and Assumptions

- Upper part contains spring mechanism to absorb landing impact up to 10 m/s

- Lower part compresses into upper part

- Landing dish allows stable landing on rough terrain

- Leg pieces made from carbon fiber

- Spring made from strengthened steel

- Four legs on STV lander as seen in diagram

Picture by:

Andrew Curtiss

Shock absorbing

Lander legs

3/24/2011

AAE 450

Spring 2011

Landing Legs Mass Summary

The combined mass of the 4 legs is:

Mass = 275.8344 kg

Volume = .1388 m3

Power = 0 kW!!

Component Material Mass (kg) Volume (m3)

Upper Leg Carbon Fiber 18.0046 0.0212

Lower Leg Carbon Fiber 39.5608 0.0096

Footpad Carbon Fiber 7.3435 0.000516

Spring Strengthened Steel 4.0497 0.0039

3/24/2011

AAE 450

Spring 2011

STV Configuration

Picture by:

Andrew Curtiss

3/24/2011

AAE 450

Spring 2011

Kim Madden Week 11 Presentation, 3/24/11

- Structures & Thermal Control

- Exploration and Rescue Rover

- Group Lead

3/24/2011

AAE 450

Spring 2011

Thermal Control System

Electronics

Conducting Plate Radiators

Heat Pump

Picture by Kim Madden

Vehicle

Heat out due to

colder temps on

Ceres, space

Heat in due to

electronics,

humans in

vehicle

Heat out via

heat pumps and

radiators

Heat in from

heater, when

needed

3/24/2011

AAE 450

Spring 2011

Heater for Exploration Rover, CTV • Heat pipe carries heat from

power supply to rover

• Internal Combustion Engine for

Rover

• Reactor for CTV

• Leads to small radiators inside

vehicle

• 1 for Rover

• 10 for CTV, near air ducts

• Radiators can be opened or

closed to let heat into vehicle at

the crew members discretion

Vehicle

Power

Source

Radiator

Picture by

Kim Madden

3/24/2011

AAE 450

Spring 2011

Circular Cross Section of Exploration

Rover

1.5 m

2.8 m Outside: Al, 1.5 cm 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

3/24/2011

AAE 450

Spring 2011

Circular Cross Section of Rescue Rover

1 m

2.4 m Outside: Al, 1.5 cm 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

-Internal pressure = 1 atm

3.4 m

3.0 m

3/24/2011

AAE 450

Spring 2011

Windshields for Rovers For 2 Windshields Exploration Rescue

Mass 882.94 kg 549.36 kg

Structural Volume 0.58 m^3 0.37 m^3

Internal Volume 19.96 m^3 10.03 m^3

½a

a

Assumptions:

-Made of Polycarbonate

-1.5 cm thick

-Weld Efficiency = 70%

3/24/2011

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