week 7 thursday (2/22) · spin rate (rpm) 2.15 2.16 arm length (m) 73.62 72.65 burn time (hours)...
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AAE 450
Spring 2011
Week 7 – Thursday (2/22)
Courtney McManus
2/24/2011
AAE 450
Spring 2011
Today’s Schedule
Group Roll Call
Section 2 Presents
Dr. Longuski shall impart wisdom upon us
Discuss Project/Vehicle Names
Group break-out/prepare for CDR
C. McManus Project Manager 2/24/2011
AAE 450
Spring 2011
2/24/2011
8:40 Courtney McManus PM
1 8:45 Trey Fortunato Aero
2 8:51 Justin Axsom Att/Con
3 8:57 Tony D'Mello Comm
4 9:03 Devon Parkos Comm
BREAK for 1 hour (meet downstairs)
5 10:35 Sonia Teran MisDes
6 10:41 Evan Helmeid MisDes
7 10:47 Graham Johnson MisDes
8 10:53 Matthew Hill Power
BREAK
9 11:10 Alex Park Power
10 11:16 Joel Lau Power
11 11:22 Kyle Svejcar Prop
12 11:28 Jillian Roberts HF
BREAK
13 11:45 Brendon White HF
14 11:51 Leonard Jackson StrcThrm
15 11:57 Alex Kreul StrcThrm
AAE 450
Spring 2011
Courtney McManus
450 Presentation – Week 7
Project Manager
Schedule, Logistics, CDR preparation
Mass to Ceres cost analysis
Rapid Cost Assessment
Advanced Mission Cost Model
Top-Level Risk Analysis
Future work
In-depth Risk Analysis
More accurate cost model
2/24/2011 McManus, Courtney Project Manager
AAE 450
Spring 2011
Risk Analysis – Fault Tree
Mission Failure
Launch Failure
○ Crew, CTV, STV
Transfer Failure
○ STV, CTV, Comm Sats
Landing on Ceres Failure
○ CTV, STV Components
Ceres Operations Failure
○ Rovers, CTV, ISPP Ops, Comm, ECLSS
Return/Re-entry Failure
2/24/2011 McManus, Courtney Project Manager
AAE 450
Spring 2011
Updated Cost Estimate
Using NASA’s Advanced Mission Cost Model
Based on masses on website
Implementation year 2030
Future work: count for inflation, operational
costs
2/24/2011 McManus, Courtney Project Manager
* Measured in year 2004 dollars
Total Cost: $129,000 million USD*
Cost/Kilogram = $ 488,130
AAE 450
Spring 2011
AAE 450: Week 7
Fortunato, Trey (Group Leader, CTV Lead, Graphic Design) Attitude Determination and Control Systems
Tasks:
Maneuver Propellant Costs
Mission Stage Transition Orientations
Artificial Gravity Spin Up and De Spin
Analyzing CTV Behavior Characteristics
Configuration of CTV
2/24/2011
AAE 450
Spring 2011
Attitude Determination and Control Systems Fortunato, Trey
CTV Configuration:
Spin Up Distribution
Total Mass 329.16 tons
Crew Side Mass 23.29 %
Counter Weight Mass 6.37 %
Center Mass 70.34 %
De-Spin Distribution
Total Mass 305.06 tons
Crew Side Mass 22.35 %
Counter Weight Mass 2.40 %
Center Mass 75.25 %
-5 0 5
-30
-20
-10
0
10
20
30
40
50
60
70
YX
Z
By: Trey Fortunato
2/24/2011
AAE 450
Spring 2011
Fortunato, Trey
CTV Spin Cost:
Attitude Determination and Control Systems
Spin Up De-Spin
Spin Rate (rpm) 2.15 2.16
Arm Length (m) 73.62 72.65
Burn Time (hours) 0.64 0.62
Total Thrust (N) 200 200
Propellant Mass (kg) 284.21 280.77
2/24/2011
AAE 450
Spring 2011 Justin Axsom
Communication
Group Lead
Human Launch Vehicle
Crew Transfer Vehicle
Earth Decent/Reentry Vehicle
Communication Satellites
Optical System Logistics
Axsom, Justin Communication 2/24/2011
AAE 450
Spring 2011 Crew Launch and Docking
Communications
Axsom, Justin Communication
Justin
Axsom
2/24/2011
AAE 450
Spring 2011 Mass, Power, and Volume of
Launch and Docking Systems
Axsom, Justin Communication
Component Mass (kg) Power (kW) Volume (m3)
Transmit Antenna 6.31 1.00 0.03
Receiving Antenna 11.2 - 0.08
Ku–band Transponder ~5.00 0.100 0.003
UHF Module 14.0 0.31 ~0.008
Total 36.5 1.41 0.121
Component Mass (kg) Power (kW) Volume (m3)
Transmit/Receiving
Antenna
8.47 0.20 3.17x10-4
UHF Transponder and
Duplexer
~5.50 0.11 ~0.008
Total 14.0 0.31 0.0083
2/24/2011
AAE 450
Spring 2011 Tony D’Mello
AAE 450: Week 7 Presentations Duties:
RF Link Budget
Rover <-> Communications Satellites
Crew Communication Tools
D’Mello, Tony Communications 2/24/2011
AAE 450
Spring 2011
Rovers
D’Mello, Tony Communications
Mass
(kg)
Power
(kW)
Volume
(m3)
Transmitter 13.23 0.48 1.94
Receiver 13.23 -- 1.94
Total 26.46 0.48 3.88
Exploration Rover Communication Hardware
Uses RF communication to
communicate with Halo Satellites
Dish sizes for transmitting and receiving
are the same because they are optimal
for the given sensor error
Dishes use a mesh grid to reduce mass
Reason for difference in power is due to
different data transfer
Exploration Rover
○ 4 HDTV channels for 4 crew members
○ 1 HDTV channel for outside camera
Rescue Rover
○ 6 HDTV channels for 6 crew members
○ No outside camera
Mass
(kg)
Power
(kW)
Volume
(m3)
Transmitter 13.23 0.57 1.94
Receiver 13.23 -- 1.94
Total 26.46 0.57 3.88
Rescue Rover Communication Hardware
2/24/2011
AAE 450
Spring 2011
Ceres Satellites – RF Communication
D’Mello, Tony Communications
Mass
(kg)
Power
(kW)
Volume
(cm3)
Transmitter –
Exploration Rover 1 0.027 0.1 8.11
Transmitter –
Exploration Rover 2 0.027 0.1 8.11
Transmitter –
Rescue Rover 0.042 0.1 19.8
Transmitter –
Halo Satellite 0.013 0.03 0.33
Receiver 0.02 -- 4.24
Total 0.129 0.33 40.59
Halo Satellites Communication Hardware
Uses RF communication with:
Exploration Rovers
Rescue Rover
ISPP Station
Partner Halo Satellite
Requires only 1 receiving dish
Each vehicle will send data at
different frequencies
While CTV is docked near ISPP
station, that station will
communicate through the CTV.
That way it won’t require a
dedicated dish on the satellites.
2/24/2011
AAE 450
Spring 2011
Devon Parkos AAE 450: Week 7 Presentations Aerodynamics Group, CTV Group, Descent Vehicle Group,
Launch Vehicle Group
Tasks Accomplished:
Analyze heating rates during aerocapture, aerobraking,
and aero-entry
Size CTV and capsule heat shields and ablative coating
for ballute tethers
Account for atmospheric uncertainty in trajectory model
and heat shield sizing
Account for lift and buoyancy from ballute
Parkos, Devon Aerodynamics
AAE 450
Spring 2011 Aerobraking Trajectories
Parkos, Devon Aerodynamics
Assumptions • CD,CTV = 2.07
• CD,B = 1.37
• CD,CAP = 0.025
• CD,PAR = 0.75
• ACTV = 182 m2
• AB = 315,000 m2
• ACAP = 12.8 m2
• APAR = 1600 m2
Without Heat Shields
• mCTV = 131 tons
• mB = 11.7 tons
• mCAP = 2.6 tons
• Vp,0 = 12 km/s
AAE 450
Spring 2011
Atmospheric uncertainty is anticipated by planning a trajectory that can capture for -15% density and sizing heat shielding that can protect from +15% density
Minimum altitude is still constrained by Qmax of Kapton Material: 2 J/cm2
Without Structural Mass: MHS,CTV = 468 kg
MHS,CAP = 19.8 kg
Conclusions Future Work
Parkos, Devon Aerodynamics
Examine tradeoff between aerobraking perigee altitude and maneuver time
More accurately model aerodynamic forces on new CTV configuration
Determine heat shield placement on CTV
Examine other tether materials
AAE 450
Spring 2011
Let’s meet again at 10:30 downstairs.
2/24/2011
AAE 450
Spring 2011 AAE 450: Week 7 Presentations
Terán, Sonia Mission Design 20
AAE 450
Spring 2011
21
Crew Transfer: inert
Terán, Sonia Mission Design
Goals DO NOT VIOLATE inert
○ Low Thrust MPD inert = 0.5
○ Kick Motor NTR inert = 0.5 – 0.7*
TOF ≤ 2 years
Assuming
MPD Isp = 5000s
NTR Isp = 1016.4s
Low Ceres Orbit = 50 km
* From Space Propulsion Analysis and Design, Humble et. al pg 461
SPEED
LIMIT
∆VC 6.908 km/s
By Trieste Signorino, based off of Professor Longuski
AAE 251 Lecture
AAE 450
Spring 2011
22
Crew Transfer: inert
Terán, Sonia Mission Design
TOF
(years)
Thrust (N) Low Thrust
∆vC
(km/s)
∆vE
(km/s) mprop,kick
(T)
mprop,LT
(T)
mprop,tot
(T)
1.09 16 4.475 4.896 38.80 42.92 81.73
1.10 16 4.625 5.996 35.18 43.05 78.24
1.12 16 4.734 3.755 32.86 43.30 76.164
Inert Mass Fraction: inert
TOF Ceres Kick Helio Low Thrust Earth Kick Geo Low Thrust
1.09 0.57 0.73 0.52 0.50
1.10 0.56 0.73 0.55 0.50
1.12 0.55 0.73 0.63 0.50
AAE 450
Spring 2011 Evan R. Helmeid
AAE 450: Week 7 Presentations Mission Design Accomplishments:
ISPP transfer trajectory Optimal elliptical case
Transfer via LCO intermediate
STV landing trajectories
Motor sizing requirements
Vehicle Group Involvement:
ISPP, Ascent/Descent, Communication, Crew Transfer Vehicle, Supply Transfer Vehicle, Rovers
Helmeid, Evan Mission Design
AAE 450
Spring 2011
Ballistic transfer trajectory LCO transfer orbit
Burn at ISPP1
Coast on elliptic trajectory
Retro burn at ISPP2
60-second hover
ΔVtot = 0.5518 km/s
Isp = 450 s
mprop = 24.66 T
mdry = 179.6 T
mwet = 204.3 T
Ascent, ISPP1 to 25km-LCO
Descent to ISPP2
60-second hover
ΔVtot = 0.5841 km/s
Isp = 450 s
mprop = 26.17 T
mdry = 179.6 T
mwet = 205.8 T
ISPP Transfer and Hover:
Move CTV from ISPP1 to ISPP2
Helmeid, Evan Mission Design
AAE 450
Spring 2011
Parameters
• Low Ceres Orbit (LCO)
= 50 km
• Isp = 450 s for Ceres
motors
• Total mprop = 22.07 T
Parameter STV1 –
to ISPP1
STV2 –
to ISPP2
Propellant
Mass [T] 11.80 10.27
Dry Mass [T] 127.9 96.93
Wet Mass [T] 139.7 107.2
ΔV [ km/s ] 0.3893 0.4446
Time of
Trajectory [s] 627.0 514.5
STV Landing Results
Helmeid, Evan Mission Design
Future Work
• Optimal trajectory program with non-zero Vy,f
• Add hover capability to STV landing
AAE 450
Spring 2011
AAE 450 Week 7 Presentations
Johnson, Graham Mission Design
AAE 450
Spring 2011
Mission Timeline and Stay Time
Johnson, Graham Mission Design
Objective: Assembly of
STV in LEO
STV
transfer
ISPP
Production
CTV Transfer (current)
Time (yrs) 3 5 5 1.73
Model Assumptions:
• Circular-Coplanar Orbits
• Assumed Timeline:
Realignment
Time:
Total Time
allowed on
Ceres
Time
(Days) 466.8 730
5000 6000 7000 8000 9000 10000 110000
50
100
150
200
250
300
350
400
time (Days)
Phase a
ngle
(D
EG
)
Phase angle History since CTV arrival; Graham Johnson
Reference Date 01/01/2020
Available time to stay on Ceres:
15.3 Years
AAE 450
Spring 2011
Future Work
Johnson, Graham
• Solidify STV transfer time/trajectory to Ceres.
• Solidify CTV transfer time/trajectory; Both to and from
Ceres.
• Calculate the g-forces applied on CTV/STV/Satellites during
Impulsive Delta-V maneuvers for Structural properties and
Human Factors.
• Finalize Crew Rendezvous time and cost with CTV while in
Geocentric spiral.
Mission Design
AAE 450
Spring 2011
Matt Hill
Power Group/ISPP
AAE 450: Week 7 Presentations
Tasks Accomplished:
Met with power group/ISPP
Set benchmarks for resource production
Selected final reactor design concept
for ISPP installation
Hill, Matt Mission Power/ISPP Stations
AAE 450
Spring 2011
• Current Reported ISPP power demands:
ISPP Power Breakdown
Hill, Matt Mission Power;/ISPP Stations
Component Power Draw (kWe)
Oven/Kiln 260
Condensor 15.1
Electrolyzer 500
RF Comms 0.05
Electronics/Sensors 0.5
LOX Tanks 4.2
LH2 Tanks 9.8
Water Tanks 150 (once only)
Harvester Operations 0.026
Total 940 kWe
AAE 450
Spring 2011
Reactor Resizing
Hill, Matt Mission Power/ISPP Stations
Assume power conversion (thermal to AC)
efficiency of 25% using stirling engines and
alternators
Scaling linearly from selected design
(1.11kWt/kg), reactor needed for 1MWe has
mass 3.6T
Based on Power/Wt ratio of existing stirling
engine, mass 3.35T
Radiator mass 1.405T
Questions?
AAE 450
Spring 2011
Start again at 11:10
2/24/2011
AAE 450
Spring 2011 Alex Park
Group Lead
AAE 450: Power Group
Tasks Accomplished:
- Supply Transfer Vehicle (STV) Power System
Design and Analysis
- Analysis and calculation on each components
- Reactor
- Shield
- Power Conversion / Piping
- Webmaster
Park, Alex Power Group
AAE 450
Spring 2011
Park, Alex Power Group
STV Power Generation Schematic
Molten Sodium Fast Reactor
5 MWe Power Generated
40% Efficiency
Thermal Photovoltaic Converter
Shielding
Tungsten-LiH-Tungsten
Gamma / Neutron Shielding
Total System Volume: 333.99 m3
AAE 450
Spring 2011
STV Power Generation Results
Park, Alex Power Group
Future Work
- Power Management and Distribution (PMAD)
- Precise tailoring of the power system dimensions to the dimensions of the STV
Mass [kg] Material
Nuclear Reactor 235
Shielding 3272.71 Tungsten-LiH-Tungsten
Radiator 3309.07 Titanium
TPV Converter 100 GaSb (Gallium Animonide)
Encasing Armor 2003.94 7 kg/m2 Material
Molten Sodium 2058.06 Molten Sodium
Total 10978.78
* Detailed Calculations attached
AAE 450
Spring 2011 Joel Lau
AAE 450: Week 7 Presentation Tasks Accomplished:
Resized Power Solutions – Both Rovers
Designed Power Sub-Systems – Both Rovers
Energy Storage
Power Distribution
Power Regulation and Control
Lau, Joel Power 36
AAE 450
Spring 2011
Rover Power Solution
Lau, Joel Power
Generator
Battery
Battery
Battery
Peak
Power
Tracker
Power
Regulator ICE
Loads
Communication – 0.48 kW
Thermal Control – 1.50 kW
Life Support – 0.12 kW
Science Equipment – 0.68 kW
Interior – 2.30 kW
Exterior Equipment – 6.10 kW
Fire Suppression – 1.48 kW
Total Peak Power – 12.66 kW
Exploration Rover Power Schematic – Joel Lau
AAE 450
Spring 2011
Rover Power Solution Specifications
Lau, Joel Power
Component Mass
(kg)
Volume
(m3)
TRL
36 kW H2/O2 ICE 93.20 0.62 3
Electric Generator 50.00 0.17 9
3x 2092 W-hr Na-S Batteries 41.82 0.09 6
Total Wet Mass: 457.01 kg
Total IMLEO: 189.82 kg
Total Volume: 1.60 m3
Component Mass
(kg)
Volume
(m3)
TRL
10 kW HFC 102.0 0.40 9
3x 2092 W-hr Na-S Batteries 41.82 0.09 6
Total Wet Mass: 151.67 kg
Total IMLEO: 144.02. kg
Total Volume: 0.5478 m3
Exploration Rover
Rescue Rover
AAE 450
Spring 2011 Kyle Svejcar
AAE 450: February 24, 2011 Tasks Accomplished:
Technical Group: Propulsion
Vehicles: ISPP, satellites
Engine Sizing for all satellites and tanks
Svejcar, Kyle Propulsion
AAE 450
Spring 2011
Earth Trailing Satellite
Svejcar, Kyle Propulsion
Mass of Satellite Components = 1241 kg
Total Mass of Satellite = 4452.88 kg
Mass fraction for orbit transfer engine = 0.32
Mass fraction for attitude engine = 0.057
Mass Propellent (kg)
Mass Engine Components (kg) Volume (m^3)
Orbit Transfer (F2/H2) 2392.6 647.26 4.79
Attitude (H2O2/HTPB) 162.2 9.824 0.1228
Total 2554.8 657.08 4.9128
AAE 450
Spring 2011
Ceres Satellites
Svejcar, Kyle Propulsion
Satellite 1 (∆V=0.374) Mass Propellent (kg) Mass Engine
Components (kg) Volume (m^3)
Orbit Transfer (MMH/N2O4) 270 10.9 0.1191
Attitude (H2O2/HTPB) 171.56 10.24 0.128
Total 441.56 55.928 0.2471
Mass of Satellite Components = 2509 kg
Total Mass of Satellite =3006.49 kg
Mass fraction for orbit transfer engine = 0.038
Mass fraction for attitude engine = 0.056
Satellite 2 (∆V=0.251) Mass Propellent (kg)
Mass Engine Components (kg) Volume (m^3)
Orbit Transfer (MMH/N2O4) 177 9.517 0.077
Attitude (H2O2/HTPB) 171.56 10.24 0.128
Total 348.56 19.75 0.205
Mass of Satellite Components = 2509 kg
Total Mass of Satellite =2877.32 kg
Mass fraction for orbit transfer engine = 0.051
Mass fraction for attitude engine = 0.056
AAE 450
Spring 2011
Jillian Roberts
AAE 450: Week 7 Presentations
Human Factors and Science
24 Feb 2011
Duties:
Crew Capsule Group Lead
Launch Vehicle Group
Crew Transfer Vehicle
Water and Waste Management Systems
Spacesuit
Radiation Shielding
Radiation Dosimeter
Topic:
Illumination
Fire Suppression
42
AAE 450
Spring 2011
Illumination
Roberts, Jillian Human Factors and Science
43
Solid State Light Module
-Composed of LEDs
-Lasts 50,000 hours
-Can be dimmed from 0-100%
-Flexible spectral power distribution:
-Emphasize yellow-red spectrum
during off-duty
-Emphasize blue spectrum to
promote alertness
-Each unit:
- 479 lumens
-3.6 kg
-~0.1 m^3
Mass: 334.8 kg
Power: 2790 W
Volume: 9.30 m^3
CTV Lighting:
Assumptions: -1000 lux for medical
wing
-500 lux for rest of CTV
AAE 450
Spring 2011
Fire Detection and Suppression
Roberts, Jillian Human Factors and Science 44
Pressurized CO2 Fire Extinguisher
PROS:
-No clean-up
-Can suppress fires even in difficult
to reach places
-Cylindrical nozzle for
bulkhead suppression ports
-Conical nozzle for open areas
-Contains no water to damage
electrical components
CONS
-Crew required to wear Portable
Breathing Apparatus (PBA) when
using extinguisher
Mass: 210.9 kg
Power: 16.3 W
Volume: 0.46 m^3
CTV Fire Detection and
Suppression System MPV
AAE 450
Spring 2011
Start again at 11:40
2/24/2011
AAE 450
Spring 2011 Brendon White
AAE 450: Week 7
Tasks Accomplished:
Computed power needed for HFS portion of
CTV
Created a CAD assembly of the CTV
Computed STV Human Factors MPV
Sketched “exploded” CTV for autonomous
rendezvous docking
White, Brendon Human Factors and Science – Slide 1
AAE 450
Spring 2011
Final CTV MPV Calculations
White, Brendon Human Factors and Science – Slide 2
Total
Mass (kg)
Total
Volume (m3)
Total Power
(KW)
CTV HFS TOTAL 15266 72.724 95.087
*For CTV Transfer Time of 2 years
*STV: 2 years living on Ceres, 2 years
getting home, 4 years for redundancy
STV SUPPLY TOTAL FOR TRIP
HOME 16227 187 0
• Updated crew quarters volume = 215.98
m3
• Attic Volume = 170 m3
• Max CTV diameter (crew area) = 10
meters
•Total height of CTV = 5.9 meters
AAE 450
Spring 2011
CTV CATIA Assembly
White, Brendon Human Factors and Science – Slide 3
AAE 450
Spring 2011 Leonard Jackson
AAE 450: Week 7 Presentations Structures and Thermal Control
ISPP and Comm. Satellites
ISPP Tank Design
Heater Storage Tank
Jackson, Leonard Structures and Thermal Control 2/24/2011 49
AAE 450
Spring 2011 Storage Tanks
(For One ISPP Station)
New Requirements:
Total 𝐿𝐻2: 376.2 tons
Total 𝐿𝑂2: 36 tons
Total Water: 40 tons Note: See attachments for tank sizes and dimensions
Alternate Solution: Take tanks from second
stage Ares V vehicles and STV
2/24/2011 50 Jackson, Leonard Structures and Thermal Control
LH2 LOX Water
Number of Tanks 13 1 1
Total Volume (m³) 5331.1 32.5 20.78
Total Mass (kg) 1759.5 5.52 23
AAE 450
Spring 2011
Required Regolith: 90 tons
Mass: 5,840 kg
66.7% Al Alloy
33.3% Polyurethane
Volume
Inner: 134.57 m³
Outer: 150.76 m³
2/24/2011 51
Heater Tank
(for one ISPP Station)
Jackson, Leonard Structures and Thermal Control
Drawing by: Leonard Jackson
AAE 450
Spring 2011 Alex Kreul
AAE 450: Week 7 Presentations
Structures & Thermal group
Crew Launch Vehicle (CLV) group
Crew Transfer Vehicle (CTV) group
Tasks accomplished & in progress:
CTV fuel tank sizing
CTV tether sizing
CTV crane sizing Kreul, Alex Structures & Thermal
AAE 450
Spring 2011
1 = kick thrust tanks (LH2)
2 = low thrust tanks (LH2)
3 = Ceres regime tanks (Lox)
4 = Ceres regime tanks (H2)
5 = attitude control tanks (N2O4)
6 = attitude control tanks (MMH)
Image by Alex Kreul
(based on config from Trey Fortunato)
CTV fuel tank sizing
Kreul, Alex Structures & Thermal
AAE 450
Spring 2011
Tank number
of tanks
V per tank
(m3)
V total
(m3)
Structural
M per tank
(kg)
Structural
M total
(kg)
1) Kick Thrust (LH2) 3 1151 3452 927 2780
2) Low Thrust (LH2) 2 953 1906 789 1578
3) Ceres Regime (Lox) 3 3.7 11.1 23.2 69.7
4) Ceres Regime (LH2) 3 10.0 30.1 36.5 109.6
5) Attitude Control (N2O4) 6 0.20 1.23 2.68 16.1
6) Attitude Control (MMH) 6 0.16 0.94 2.14 12.8
TOTAL 5,401 m3 4,566 kg
Carbon composite pressure vessel
Mylar multi-layer insulation
.25 MPa tank pressure (to be updated)
6g max acceleration
CTV fuel tank sizing
Kreul, Alex Structures & Thermal
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