Introduction
AAE 450 – Spring 2004
Project HOMER
Humans Orbiting Mars for Exploration and Research
Brady Kalb
Spring 2004 AAE450: Slide 1
Homer Heavy Lift Launch Vehicle
2nd Stage
3rd Stage
57 m
89 m
44 m
Chris Ulrich, Chris Krukowski, Frank Hankins, Nikolaus Ladisch, Marina Mazur, Matt Maier
Spring 2004 AAE450: Slide 2
HOMER LAUNCH VEHICLES
HEAVY LIFT LAUNCH VEHICLE MASS BREAKDOWN
Initial Mass
(kg)
Final Mass (kg)
Propellant Mass
(kg)
1st Stage Main
Core
2,940,000
2,680,000
465,000
2nd Stage Main
Core
2,480,000
461,000
2,020,000
344,000
238,000
106,000
1,710,000
203,000
1,500,000
3rd Stage
Strap-on Boosters
Chris Ulrich, Chris Krukowski, Frank Hankins, Nikolaus Ladisch, Marina Mazur, Matt Maier
Spring 2004 AAE450: Slide 3
CRV: Aerodynamic Stability
alpha =
alpha =
alpha =
alpha =
alpha =
alpha =
alpha =
alpha =
alpha =
alpha =
alpha =
alpha =
alpha =
alpha =
alpha =
Static Margin Mach 29.5
1
Equation used in Trim line calculations:
0.8
0.6
0.2
SM (%)
Cm  Cm0  CZ ( xMRC  xCG )  C X ( zMRC  zCG )
0.4
0
-0.2
110.1365
115.1365
120.1365
125.1365
130.1365
135.1365
140.1365
145.1365
150.1365
155.1365
160.1365
165.1365
170.1365
175.1365
180.1365
-0.4
Front (1)
-0.6
-0.8
-1
0
0.1
0.2
0.3
0.4
0.5
0.6
Xcg (delX/length)
0.7
0.8
0.9
1
Static Margin vs. Various Mach
150
Alpha=140
Alpha=145
Alpha=150
a = 144deg
Static Margin (%)
100
50
Aft (0)
0
5
10
Rebecca Karnes
Spring 2004 AAE450: Slide 4
15
Mach #
20
25
30
CRV: LES Sizing and Components
Rocket Structure
• Launch Escape Motor
• Pitch Control Motor
• Tower Jettison Motor
Launch Escape Tower
Boost Protective Cover
Heather Dunn
Spring 2004 AAE450: Slide 5
CRV: LES and Parachute Mass
Parachute Recovery System
Component
Drogues
Property
Value
Number
Diameter (each) [m]
Area (each) [m2]
2
5.5
23.5
Number
Diameter (each) [m]
Area (each) [m2]
3
33.6
888.0
Main Parachutes
Launch Escape System
Component
Mass (kg)
Launch Escape Tower
517
Launch Escape Motor
2132
Boost Protective Cover
430
Pitch Control Motor
23
Tower Jettison Motor
50
Total
3152
Heather Dunn
Spring 2004 AAE450: Slide 6
Transport Vehicle
Thrusting Mode after leaving Earth
Devin Fitting, Dave Goedtel, Ben Toleman, Debanik Barua
Spring 2004 AAE450: Slide 7
Transport Vehicle
Storage view with airlock
Devin Fitting, Dave Goedtel, Ben Toleman, Debanik Barua
Spring 2004 AAE450: Slide 8
Transport Vehicle
• Aerocapture Mode
– Radiators retracted
– Comm. Antenna
Retracted
– Vehicle collapsed
Spring 2004 AAE450: Slide 9
Human Factor Mass Summary
# of Items
Unit Mass
[kg/unit]
Total Mass
[kg]
1st Floor Total
34
-
1280
See Table D-2 for list
2nd Floor Total
20
-
1600
See Table D-3 for list
3rd Floor Total
27
-
3420
See Table D-4 for list
4th Floor Total
1
-
400
See Table D-5 for list
Stored Items Total
22,500
-
16,900
Includes 11,600 kg of consumables
See Table D-6 for list
Other Items Total
4
-
12,700
Includes 11,800 of kg consumables
See Table D-7 for list
Installation Margin for
Zero g
-
0.4
14,500
Component
Total
50,800
Total with 5% Growth
53,300
(HF Consumable Mass)
23,400
(HF Dry Mass)
29,900
Comments
Pat Nelson, Steve Blaske, Theresa McGuigan, Wade McMillan
Spring 2004 AAE450: Slide 10
Major Components Contained on the First Floor
# of Items
Unit Mass
[kg/unit]
Total Mass
[kg]
Bed
4
46
184
Washing Machine
1
100
100
Dryer
1
60
60
Desk
4
15
60
Chair
8
5
40
Shower
1
75
75
Sink
1
8
8
WCS
1
112
112
Multi-gym
1
200
200
Stepper
1
136
136
Treadmill
1
150
150
Gym Equipment
1
25
25
Table
1
15
15
Couch
1
45
45
TV
4
10
40
1st Floor Component
Comments
Waste Collection System
Pat Nelson, Steve Blaske, Theresa McGuigan, Wade McMillan
Spring 2004 AAE450: Slide 11
Major Components Contained on the Second Floor
# of Items
Unit Mass
[kg/unit]
Total Mass
[kg]
Microwave
2
35
70
Dishwasher
1
40
40
Sink
1
15
15
WCS
1
112
112
Small Sink
1
8
8
Med Suite
1
1000
1000
Bed
1
55
55
Desk
1
15
15
Table
1
15
15
Chairs
5
5
25
TV
4
10
40
Scientific Payload
1
200
200
2nd Floor Component
Comments
Waste Collection System
Not Much! (i.e. biomass growth
chamber, biogen water recycling)
Pat Nelson, Steve Blaske, Theresa McGuigan, Wade McMillan
Spring 2004 AAE450: Slide 12
Major Components Contained on the Third Floor
# of Items
Unit Mass
[kg/unit]
Total Mass
[kg]
Console
5
130
650
Table
2
15
30
Chair
7
5
35
Mainframe
2
200
400
Large TV
1
30
30
Work Table
1
20
20
TV
2
10
20
Airlock
1
400
400
WPA
2
658
1320
OGA
2
140
280
4BMS
2
120
240
3rd Floor Component
Comments
Includes chair for console
Command TV
Backup Unit
Pat Nelson, Steve Blaske, Theresa McGuigan, Wade McMillan
Spring 2004 AAE450: Slide 13
Stored Components
Comments
# of Items
Unit Mass
[kg/unit]
Total Mass
[kg]
Food*
3600
2.3
8280
2nd Floor
Cleaning Supplies*
900
0.25
230
Evenly divided between floors
4
5
20
2nd Floor
Bathroom Supplies*
3600
0.05
180
1st and 2nd
Backup Bathroom Bags
3600
0.25
900
1st and 2nd
4
1.8
8
1st Floor
3600
0.075
270
1st Floor
Clothing
4
90
360
1st Floor
Recreation Items
1
1000
1000
1st Floor
Personal Items
4
50
200
1st Floor
Vacuum
1
13
13
1st Floor
Disposable Wipes*
3600
0.3
1080
2nd Floor
Trash Bags*
3600
0.05
180
Evenly divided between floors
4
20
80
Includes diskettes, ziplocks, tape…
(Evenly Divided between floors)
Component
Cooking Supplies
Personal Hygiene Kit
Hygiene Supplies*
Operational Supplies
Pat Nelson, Steve Blaske, Theresa McGuigan, Wade McMillan
Spring 2004 AAE450: Slide 14
Stored Components (Continued)
# of ItemsUnit
Mass[kg/unit]
Total
Mass[kg]
Restraints
1
100
100
For zero g environment
Hand Tools
1
300
300
Primarily 3rd floor
Test Equipment
1
500
500
3rd Floor
Other Maintenance
Equipment
1
1000
1000
3rd Floor
Photography
1
120
120
1st Floor
Fire Suppression
4
5
20
Evenly divided between floors
EVA Tools
1
123
120
3rd and 4th
Manuerving Unit
2
35
70
4th Floor
EVA Suits
4
135
540
Primarily 4th
Med Consumables*
1
500
500
2nd Floor
Crew
4
70
280
Evenly divided between floors
Water Tank Spares
1
329
329
Hab Exterior
Waste Spare
1
56
56
3rd Floor
Atmosphere Spare
1
130
130
3rd Floor
Component
Comments
Pat Nelson, Steve Blaske, Theresa McGuigan, Wade McMillan
Spring 2004 AAE450: Slide 15
Stored Components
Major Components Contained on the Fourth Floor
4th Floor
Component
Airlock
# of Items
Unit Mass
[kg/unit]
Total
Mass
[kg]
1
400
400
Comments
Primary Unit
Other Components
Component
# of Items
Unit Mass
[kg/unit]
Total
Mass
[kg]
Water Tanks
1
204
204
Water*
1
10199
10,199
Air Tanks
1
743
743
Total Gas*
1
1566
1566
Comments
Allotted Tank Mass
Allotted Tank Mass
Pat Nelson, Steve Blaske, Theresa McGuigan, Wade McMillan
Spring 2004 AAE450: Slide 16
Air Subsystem
Air Subsystem Design Values
Value
Unit
Total Mass
4,500
kg
Total Volume
7.0
m3
Total Power
2.6
kW
Totals
Atmosphere Composition and Pressure
Air Subsystem Breakdown
Gas
Pressure [kPa]
Component
Mass [kg]
p(O2)
19.50
Total Gas
1,600
p(CO2)
0.12
Mechanical Systems
500
p(N2)
50.38
Tanks
700
Total Pressure
70.30
Spares
300
Pat Nelson, Steve Blaske, Theresa McGuigan, Wade McMillan
Spring 2004 AAE450: Slide 17
Waste & Water Subsystem
Water Mass for Mission
WCS Specifications
Spec.
Value
Units
Required Mass for
Recovery of Recycling Losses
9600
kg
Spec.
Value
Units
Mass
112
kg
Volume
0.55
m3
Mass of Initial System Charge
120
kg
Power
375
Watts
5 % Margin for Leakage / Spills
490
kg
Total Mass of Water
10,200
kg
Packing Factor
1.02
Daily Water Budget
Spec.
Value
Units
Water Input
118
kg/d
Water Output
119
kg/d
Percent Recycled
90
%
Total Loaded Mass of Water
10,400
kg
Mass Recycled
107
kg/d
Volume of Water [0.001 m3/kg]
10.4
m3
Difference between Required
and Recycled
10.5
kg/d
WPA Specifications
Spec.
Value
Units
Mass
658
kg
Volume
2
m3
Power
915
Watts
Pat Nelson, Steve Blaske, Theresa McGuigan, Wade McMillan
Spring 2004 AAE450: Slide 18
Artificial Gravity
Gravity Gradient relative to 9.81 m/s2
Floor
Transit Gravity
Martian Orbit Gravity
1st
1
0.38
2nd
0.92
0.34
3rd
0.83
0.29
Pat Nelson, Steve Blaske, Theresa McGuigan, Wade McMillan
Spring 2004 AAE450: Slide 19
Volume Comparisons
Comparison
Volume per Person
[m3/p]
Comments
Small Office
15
Habitable volume per person
Recreational Vehicle
27.5
Habitable volume per person
Naval Submarine
145
Pressurized volume per person
Skylab
100
Pressurized volume per person
Mir
124
Pressurized volume per person
ISS
142
Pressurized volume per person
Pat Nelson, Steve Blaske, Theresa McGuigan, Wade McMillan
Spring 2004 AAE450: Slide 20
Habitat Module
10.084 m
2.58 m
10.5 m
Debanik Barua, Masaaki Atsuta, Jamie Krakover, Rachel Malashock, George Mseis, Daniel Nakaima
Spring 2004 AAE450: Slide 21
Storage Module
Doors for CRV/Landers
10.084 m
10.5 m
Debanik Barua, Masaaki Atsuta, Jamie Krakover, Rachel Malashock, George Mseis, Daniel Nakaima
Spring 2004 AAE450: Slide 22
Effect of Thickness on Hoop Stress
Debanik Barua, Masaaki Atsuta, Jamie Krakover, Rachel Malashock, George Mseis, Daniel Nakaima
Spring 2004 AAE450: Slide 23
Buckling Analysis
Debanik Barua, Masaaki Atsuta, Jamie Krakover, Rachel Malashock, George Mseis, Daniel Nakaima
Spring 2004 AAE450: Slide 24
Column Configuration and FEM Analysis
2.00 m
1.00 m
R 0.30 m
0.02 m
R 0.20 m
2.58 m
R 0.20 m
0.10 m
0.75 m
1.50 m
Max. von Mises Stress = 9.65×107 N/m2
Max. Principal Stress = 9.74×107 N/m2
Max. Displacement = 1.36×10-4 m
Mass = 916.34 kg
Debanik Barua, Masaaki Atsuta, Jamie Krakover, Rachel Malashock, George Mseis, Daniel Nakaima
Spring 2004 AAE450: Slide 25
Brace Configuration and FEM Analysis
Max. von Mises Stress = 3.61×107 N/m2
Max. Principal Stress = 3.72×107 N/m2
Max. Displacement = 6.25×10-4 m
Mass = 65.80 kg
Debanik Barua, Masaaki Atsuta, Jamie Krakover, Rachel Malashock, George Mseis, Daniel Nakaima
Spring 2004 AAE450: Slide 26
Floor Configuration and FEM Analysis
Max. von Mises Stress = 9.52×106 N/m2
Max. Principal Stress = 9.38×106 N/m2
Max. Displacement = 1.40×10-4 m
Mass = 9.76×103 kg
Debanik Barua, Masaaki Atsuta, Jamie Krakover, Rachel Malashock, George Mseis, Daniel Nakaima
Spring 2004 AAE450: Slide 27
CRV and Lander Holders Configuration
Lander Holder
CRV Holder
Debanik Barua, Masaaki Atsuta, Jamie Krakover, Rachel Malashock, George Mseis, Daniel Nakaima
Spring 2004 AAE450: Slide 28
CRV and Lander Holders Analysis
Debanik Barua, Masaaki Atsuta, Jamie Krakover, Rachel Malashock, George Mseis, Daniel Nakaima
Spring 2004 AAE450: Slide 29
Margin of Safety (MS)
• Surface Crack Propagation
• Assumptions:
- Leak before break
- a/c = 1.0
- a/t = 1.0
- a/b = 0.1
 design 
p0 r
 2.55 108 N 2
m
t
Surface Crack Propagation
(Fig 8.3 from Fundamentals of Structural Integrity by Alten F. Grandt)
K = 36.26 MPa-m1/2 for Al 2219-T851
K   allow
a
a a c 
 M f  , , ,     allow  6.28 108 N 2
m
Q
t c b 
 allow
MS 
 1  147%
 design
Debanik Barua, Masaaki Atsuta, Jamie Krakover, Rachel Malashock, George Mseis, Daniel Nakaima
Spring 2004 AAE450: Slide 30
Hoytube Design
• 6 Hoytubes within the bundle
• 5 primary lines per Hoytube
– Most of load bearing
capability
• 8 Secondary lines per Hoytube
– Initially slack, load bearing
in case of damaged
primary lines
• High survivability
– 100 % > 70 years
Debanik Barua, Masaaki Atsuta, Jamie Krakover, Rachel Malashock, George Mseis, Daniel Nakaima
Spring 2004 AAE450: Slide 31
Component Masses
Hab Component Mass (kg)
Hab Component
Mass (kg)
Stringers
360
End Caps
4,500
Rings/Frames
620
Outer Shell
1,880
Columns
2,750
Inner Wall
3,980
Braces
1,180
Micrometeorite Protection
2,500
Airlocks
3,260
Floor Partitions
15,570
Debanik Barua, Masaaki Atsuta, Jamie Krakover, Rachel Malashock, George Mseis, Daniel Nakaima
Spring 2004 AAE450: Slide 32
Layering System
Layering
Al 6061 Bumper
MLI
Polyethylene
Al 2219-T851 Shell
Thickness
2 mm
6.4 mm
7 cm
2 mm
Debanik Barua, Masaaki Atsuta, Jamie Krakover, Rachel Malashock, George Mseis, Daniel Nakaima
Spring 2004 AAE450: Slide 33
Rigid Body Model
4.38 m
9.31 m
Stringer
Ring/Frame
Debanik Barua, Masaaki Atsuta, Jamie Krakover, Rachel Malashock, George Mseis, Daniel Nakaima
Spring 2004 AAE450: Slide 34
Power Subsystems Breakdown (Primary Power)
Subsystem
Power Allotted
(kWe)
Percentage of
Total Power
Human Factors
23
11.5%
Thermal
20
10%
5
2.5%
Communications
20
10%
Propulsion
0.8
0.4%
Structures
1.5
0.8%
0
0%
Margin
9.7
4.8%
Continuous Power Subtotal
80
40%
Dynamics and Controls
120
60%
Total
200
100%
Power
Aerodynamics
Ryan Spalding, Reuben Schuff, Justin Tucker
Spring 2004 AAE450: Slide 35
Power Cable
Ryan Spalding, Reuben Schuff, Justin Tucker
Spring 2004 AAE450: Slide 36
Power Cable Mass
Mass Breakdown for Components of Power Cable
Copper
Density [kg/m^3]
Silicone
Shielding
8920
1150
9000
1.70E-08
NA
NA
Length [m]
75
75
75
Cross-section Area [mm^2]
14
19.2
25.4
Mass per Wire [kg]
9.4
1.7
NA
4
4
NA
37.4
6.6
17.2
NA
NA
3
Resistivity [Ohm-m]
Number of Wires per Bundle
Mass per Bundle [kg]
Number of Bundles
Total Mass of Cable [kg]
Ryan Spalding, Reuben Schuff, Justin Tucker
Spring 2004 AAE450: Slide 37
183.7
Fuel Cell System Mass
Mass Breakdown of Fuel Cell System
Item
3
Mass (kg)
Volume (m )
Each Fuel Cell
118
0.16
Fuel Cells (5)
590
0.8
Each LOX Tank
115
0.53
LOX Tanks (2)
230
1.06
Each LH2 Tank
131
1.09
LH2 Tanks (2)
262
2.18
Total Hardware
1082
4
LOX Fuel
893
0.77
LH2 Fuel
112
1.59
Total Fuel
1005
2.36
2100
Ryan Spalding, Reuben Schuff, Justin Tucker
4
Total System
Spring 2004 AAE450: Slide 38
Power Subsystems Breakdown
(Secondary Power)
Location of Power Use
Power Supplied (kWe)
Tether Winch
7.5
Human Factors Considerations
10
Communication/Navigation
7
Thermal Concerns
5
Margin
1
Total (without winch)
23
Total (with winch)
Location of Power Use
30.5
Power Supplied (kWe)
Human Factors Considerations
4
Communication/Navigation
4
Thermal Concerns
5
Margin
1
Total
14
Ryan Spalding, Reuben Schuff, Justin Tucker
Spring 2004 AAE450: Slide 39
Breakdown of Fuel Cell System
(Duration and Power Supplied)
Interval
Time (hr)
Power Supplied
(kWe)
Power Capacity
(kWe-hr)
1 Procedure
3
30.5
91.5
Total Required: 6
18
30.5
549
Margin: 14
42
30.5
1281
Total: 20
60
30.5
1830
First Burn
1.5
23
34.5
Second Burn
1
23
23
Third Burn
0.5
23
11.5
Margin
2
23
46
Total
5
23
115
Aerocapture:
2
3
6
Total
n/a
n/a
1950
Tether Deployment
and Retraction:
Main Engine Burn:
Ryan Spalding, Reuben Schuff, Justin Tucker
Spring 2004 AAE450: Slide 40
Mass Breakdown of Power Distribution System
Components:
Plasma Contactors (Ground)
159
Transformers:
Large
670
Small Scale
5
Regulators, Converters, charge controllers,etc
1037
TOTAL COMPONENTS
1872
TOTAL WIRING
3461
TOTAL DISTRIBUTION SYSTEM
5330
Ryan Spalding, Reuben Schuff, Justin Tucker
Spring 2004 AAE450: Slide 41
Power Loss in Tether
Energy Balance at Outter
Insulation Surface:
q net  q solar  qemitted 
Power Loss
Wire Surface Area
Energy Balance at Inner
Insulation Surface:
Power Loss
 q solar  qemitted
Wire Surface Area
Melanie, Matthew Branson, Lucia Capdevila, Alessandro Ianniello, Robert
Silosky
Manning
Spring 2004 AAE450: Slide 42
Cooling Loop Design
• Propulsion Module
– Two phase H2O loop
– Mass flow rate = 0.04 kg/s
– Pressure = 2 atm
T1 = 130.8 oC
H2O vapor
380 kW
From
Engines
380 kW
HX
P
• Habitat Module
– Single phase liquid NH3 loop
– Mass flow rate = 0.08 kg/s
– Supply temperature = 4.4 oC
T2 = 130.8 oC
H2O liquid
P
HX
Spring 2004 AAE450: Slide 43
33 kW
T1 = 83 oC
P
HX
T2 = 4.4 oC
T2 = 4.4 oC
33 kW
T1 = 83
oC
Panel Design
• Panel Design
3.81 mm
0.58 mm
– Beryllium fins (k = 220 W/m-K)
– Z-93 white paint coating (e = 0.92)
10 cm
Spring 2004 AAE450: Slide 44
fin
heat
pipe
Radiator Mass Breakdown
Propulsion module
Habitat Module
Panel
781 kg
365 kg
Support structure
3780 kg
1763 kg
Total
4561 kg
2128 kg
Spring 2004 AAE450: Slide 45
Timeline
•
•
•
•
•
•
•
•
•
•
Early November 2009 – 500 km circular orbit at 23.45º inclination
Late November 2009 – Finite burn for trans-Mars injection, Δv = 4.50
km/s
Mid January 2010 – Tether deployed, spin-up maneuver, ω = 5 rpm
Early June 2010 – Spin-down maneuver, EVA performed, prepare for
aerocapture
Mid June 2010 – Mars atmospheric probes released
Mid July 2010 – Aerocapture into 14 day elliptic orbit around Mars, e
= 0.97
Late July 2010 – First Mars Lander released, landing at 1.98ºS,
353.82ºE
Early August 2010 – Second Mars Lander released, landing at
8.92ºN, 205.21ºW
Mid August 2010 – Apo-twist maneuver
Mid September 2010 – Spin-up maneuver, simulate Mars gravity
Allison Bahnsen, Daniel Grebow, Kelli Hsieh, Steven Lambert, Joseph Paunicka,
Brian Pramann
Spring 2004 AAE450: Slide 46
Mars Aerocapture: Capturing the Corridor
•
•
Vehicle Characteristics Unchanged
Entry Corridor Density Uncertainties
Parameter
Variation
Standard Dev.
-3, 0 and 3
Dust Level
Low, Mod, High
Time of Day
0-24 hrs (4 hr incr.)
•
Nominal Flight Path Angles [LU, LD]
[-9.43º, -8.1065º]
% Cases Captured: 54 Total
St. Dev
% LU Capt.
% LD Capt.
-3
83.33 %
83.33 %
0
100 %
100 %
3
100%
33.33%
Ellipsled
Image taken from R.
Whitley and C.
Cerimele
Ryan Whitley
Spring 2004 AAE450: Slide 47
Spin-up/Spin-down Specifics
Spin-Up
ΔV (m/s) Time (days)
Spin-down
ΔV (m/s) Time (days)
Trans-Mars
Hab side
28.8
41.5
28.8
41.5
Propulsion side
38.2
41.5
38.2
41.5
Hab side
10.4
29.5
10.4
28
Propulsion side
13.6
29.5
13.6
28
Hab side
28.8
22.1
28.8
20.6
Propulsion side
57.64
22.1
57.64
20.6
Mars Orbit
Trans-Earth
Allison Bahnsen, Daniel Grebow, Kelli Hsieh, Steven Lambert, Joseph Paunicka,
Brian Pramann
Spring 2004 AAE450: Slide 48
Hall Effect Thruster Placement
Allison Bahnsen, Daniel Grebow, Kelli Hsieh, Steven Lambert, Joseph Paunicka,
Brian Pramann
Spring 2004 AAE450: Slide 49
Trans-Earth Injection: Finite Burn
• Early November 2009 – Initial
Earth parking orbit.
• Late November 2009 – TransMars injection, 1.34 hour burn
time.
–
Impulsive: ΔV = 3.55 km/s.
–
Finite: ΔV = 4.50 km/s.
Daniel Grebow, Allison Bahnsen, Kelli Hsieh, Steven Lambert, Joseph Paunicka,
Brian Pramann
Spring 2004 AAE450: Slide 50
Finalized Orbital Parameters
a
(km)
e
rp
(km)
ra
(km)
v∞
(km/s)
ΔV
(km/s)
P
TOF
(days) (days)
Trans-Mars
1.89e8 0.21 1.50e8 2.28e8
2.94
3.55
518
259
Hyperbolic
Arrival
8.44e3 1.43 3.45e3
2.64
(ΔVeq = 0.52)
-
-
Post-Capture
Elliptical
1.17e5 0.97 3.45e3 2.30e5
2.67
1.6e-3
13.99
6.99
Mars Parking 1.17e5 0.97 3.60e3 2.30e5
5.01
3.8e-2
14.00
336
“Parabolic”
Departure
2.01e8 1.00 3.60e3
2e-4
ΔVcr = 2.65
-
-
Trans-Earth
1.89e8 0.21 1.50e8 2.28e8
2.93
0.48
518
259
-
-
TOTALS
Total Mission Time (yrs)
2.36
Total Main Engine ΔV (km/s)
7.88
Daniel Grebow, Allison Bahnsen, Kelli Hsieh, Steven Lambert, Joseph Paunicka,
Brian Pramann
Spring 2004 AAE450: Slide 51
Aerocapture into 14-day Elliptic Orbit
Mars Elliptical Orbit
3,600 km x 230,000 km
v∞
(km/s)
ΔV
(km/s)
8
Trans-Mars Injection
2.94
3.55
6
Periapsis Raise Maneuver
2.67
0.71
4
Trans-Earth Injection
5.01
3.8e-2
Correction Maneuver
2e-4
2.65
TOTAL
6.95
Aerocapture with 14-Day Elliptical Parking Orbit
4
Cartesian Y, y [km]
x 10
Hyperbolic Arrival
Post-Capture Orbit
Elliptical Parking Orbit
'Parabolic' Departure
2
0
-2
-4
Possible methods to reduce Δvcr:
• Out-of-plane hyperbolic arrival at Mars.
• Rotation of the line of apsides and precession
of the line of nodes due to Mars’ oblateness.
• Apo-twist maneuvering.
• Apply correction maneuver before periapsis.
-6
-8
-2
-1.5
-1
Cartesian X, x [km]
-0.5
0
Daniel Grebow, Allison Bahnsen, Kelli Hsieh, Steven Lambert, Joseph Paunicka,
Brian Pramann
Spring 2004 AAE450: Slide 52
5
x 10
Apo-Twist
dw/dt=(3*n*J2*Rplanet2(4-5*sin2(i)))/(4*a2(1-e2))
Orbital Plane
63.4 deg
Ecliptic Plane
25.19 deg
“Squishy”
Mars
Daniel Grebow, Allison Bahnsen, Kelli Hsieh, Steven Lambert, Joseph Paunicka,
Brian Pramann
Spring 2004 AAE450: Slide 53
Zubrin’s Trajectory
Zubrin's "Athena" Trajectory
Earth Orbit
Mars Orbit
Initial Hohmann Transfer
Spacecraft Intermediate Orbit
Final Hohmann Transfer
7
Cartesian Z, z [km]
x 10
6
4
2
0
-2
2.5
2
1.5
1
2
0.5
0
1
8
x 10
8
x 10
-0.5
-1
0
-1.5
-1
Cartesian Y, y [km]
-2
-2
-2.5
Cartesian X, x [km]
Daniel Grebow, Allison Bahnsen, Kelli Hsieh, Steven Lambert, Joseph Paunicka,
Brian Pramann
Spring 2004 AAE450: Slide 54
Aerodynamics: Equations of Motion
h  V sin 
 sin 
D
V   
m (rmars  h) 2
 cos 

L cos  
V2

 


2
 (rmars  h) (r
 V
mV
mars  h) 

L sin 
V
 

cos  cos tan 
mV cos  rmars  h
 
V
rmars  h
cos  sin 
  V cos  cos

(rmars  h) cos 
Ryan Whitley
Spring 2004 AAE450: Slide 55
Aerocapture: Final Altitude Profile
Ryan Whitley
Spring 2004 AAE450: Slide 56
Aerocapture: Final Velocity Profile
Ryan Whitley
Spring 2004 AAE450: Slide 57
Aerocapture: Final G-load Profile
Ryan Whitley
Spring 2004 AAE450: Slide 58
Probe: Equations Used
•
•
•
•
Ballistic Coefficient = m/Cd S
V = Ve exp (1/2Z 1/BC rho/sin gamma (exp –Zh))
dv/dt = -1/2 1/bc rho V²
Qrate = k (rho/Rn U/1000)³
Ayu Abdullah
Spring 2004 AAE450: Slide 59
Probe Trajectory
(Trajectory found using data from code by Ryan Whitley and Bob Manning)
Altitude versus Time
Altitude (km)
100
50
0
-50
0
50
100
150
200
250
300
Time (s)
Velocity versus Time
350
400
450
Velocity (km/s)
5
4
3
2
80
90
100
110
120
Time (s)
130
Ayu Abdullah
Spring 2004 AAE450: Slide 60
140
150
Probe Trajectory
(Trajectory found using data from code by Ryan Whitley and Bob Manning)
Altitude versus Range
Altitude (km)
100
50
0
-50
0
100
200
100
200
300
400
500
Range (km)
Velocity versus Range
600
700
800
600
700
800
Velocity (km/s)
6
4
2
0
0
300
400
500
Range (km)
Ayu Abdullah
Spring 2004 AAE450: Slide 61
Probe Characteristics




Powered by 2 non-rechargeable lithium-thionyl cloride batteries of 600 miliamp hours, 6
– 14 volts for 1-3 days.
Probes encased in aeroshells made of ceramic material
Probes will contain batteries, accelerometers, sun sensor, temperature sensor,
communications equipment.
Propulsion system¹
Main engine – Marquadt R6 – C
Two tanks using fuel – N2O4, oxidizer – MMH
3 Retro-rockets which provide Δv = 16 m/s
¹ Propulsion system designed by Nikolaus Ladisch using trajectory from module designed by Brian Pramann
Ayu Abdullah
Spring 2004 AAE450: Slide 62
Visualization of the Mass Breakdown
S1
S2
S3
S4
S5
S6
C1
C2
C3
C4
C5
C6
Matthew Branson, Bob Manning, Alessandro Ianniello, Melanie Silosky, Lucia Capdevila
Spring 2004 AAE450: Slide 63
Ablator Materials4
SLA-561V is a mixture of Silicone, silica microballons, corks and
silica glass fibers that is injected into a glass reinforced polymide
honeycomb.
Ablator Materials is used to help cut down on weight. The material is
burnt up while entering into an atmosphere to remove some of the
heat that is generated while entering.
Matthew Branson, Bob Manning, Alessandro Ianniello, Melanie Silosky, Lucia Capdevila
Spring 2004 AAE450: Slide 64
Composites Purpose in
Heat shields
• The main purpose is for Strengthing the heatshield when
dealing with such high thermal loads
• Si-C (Silcon-Carbide) is used for its VERY high (2800oK)5
melting point while still maintaning its strength (200-350
MPa)5
• C-C (Carbon-Carbon) is used for its very high (20600K)5
Matthew Branson, Bob Manning, Alessandro Ianniello, Melanie Silosky, Lucia Capdevila
Spring 2004 AAE450: Slide 65
References
1)
4)
David G. Gilmore, Spacecraft Thermal Control Handbook, The Aerospace
Press, El Segundo, CA., 2002
Charles D. Brown, Elements of Spacecraft Design, AIAA Education Series,
Castle Rock, CO, 2002
Wiley J. Larson and Linda K Pranke, Human Spaceflight, The McGraw-Hill
Companies, inc., New York, NY
K. Sermeus, Euroavia / Mission to Mars Symposium
5)
http://www.ultramet.com/old/therm.htm
6)
7)
Soddit Matlab code written by Damon Landau
Sandia One-Dimensional Direct and Inverse Thermal Code (Soddit), Sandia
National Laboratories, Albuquerque, New Mexico, 1990
Professor Schnider
2)
3)
8)
Spring 2004 AAE450: Slide 66
Lander Placement
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 67 Dan Nakaima, Ben Phillips
Lander Separation
• Release of First
Lander
– Correction Dv =
1.01 m/s
• Release of Second
Lander, waiting
half a sol:
– Correction Dv =
1.17 m/s
Trajectory of 1st Lander
Transport Trajectory
Trajectory of 2nd Lander
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 68 Dan Nakaima, Ben Phillips
Rover Communication
• Can view half of Mars for 99.73% of the
time
• Meets needs of communications
– Equatorial Landings Sites are suitable
Transport Orbit
Swath Width
Communication Availability By: Allison Bahnsen
8000
6000
Cartesian y [km]
4000
2000
0
Equator
-2000
-4000
-6000
-8000
-5000
0
Cartesian x [km]
5000
View from Spacecraft
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 69 Dan Nakaima, Ben Phillips
Rover Communication – Swath Width
• Sw = 2*a*Rs
• At apoapsis, Sw =
10,572 km
• At periapsis, Sw =
2,276 km
• Calculated the
distance when Sw =
2*3397km to find
when we could see the
whole planet
RS
Spring 2004 AAE450: Slide 70
a
b
ra
Rover Landing Sites
Terra Meridiani
Athabasca Valles
|203 W
| 205W
|207 W
10 N_
9 N_
8 N_
1.98° S, 6.18° W
8.92° N, 205.21° W
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 71 Dan Nakaima, Ben Phillips
Details on Cruise Stage
Solar Panels
Thrusters
Heaters
Prop. Tank
Sun Sensor
Star Scanner
5m
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 72 Dan Nakaima, Ben Phillips
Parachute System
Variable Name
Material
Specific Weight
WC (canopy)
Nylon/Kevlar
.0115 lb/ft2
WSL (suspension
lines)
Kevlar
.0035 lb/ft/1000 lb
strength
WRT (radial tape)
Kevlar
.0035 lb/ft/1000 lb
strength
WR (riser)
Kevlar
.0035 lb/ft/1000 lb
strength
Parameters
Drogue
Lander
SO [m2]
170
385
DO [m]
10.4
16.7
NSL
48
48
LSL [m]
16
23
NR
1
5
LR [m]
5
3
NG
48
48
Volume [m3]
.021
.039
Total mass
[kg]
17
32
Upper portion of Lander and
parachute cables
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 73 Dan Nakaima, Ben Phillips
Aeroshell Ballistic Trajectory
Altitude versus Velocity
Altitude (km)
Entry parameters –
Ventry = 4.896 km/s
Gamma = 4.596 degrees
Ballistic coefficient
= 99.07 kg/m^2
Maximum Heating Rate
= 322.03 W/cm^2
Altitude of Maximum Heating
Rate =35.87 km
• Maximum Deceleration = 4.4
Earth G’s
• Altitude of Maximum
Deceleration = 26.31 km
100
50
0
0
0.5
1
1.5
2
2.5
3
Velocity (km/s)
3.5
4
4.5
5
Altitude versus Deceleration
150
Altitude (km)
•
•
•
•
•
•
•
•
150
100
50
0
0
0.5
1
1.5
2
2.5
3
Deceleration (Earth Gs)
3.5
4
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 74 Dan Nakaima, Ben Phillips
4.5
Aeroshell Design
• Cd of Aeroshell =1.69
• Mass of Aeroshell = 435 kg
• -Heatshell = 230 kg
- Backshell = 205 kg
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 75 Dan Nakaima, Ben Phillips
Lander Trajectory
Altitude versus Time
Altitude (km)
100
50
0
-50
0
50
100
150
200
250
300
Time (s)
Velocity versus Time
50
100
150
350
400
450
350
400
450
Velocity (km/s)
5
4
3
2
1
0
0
200
250
Time (s)
300
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 76 Dan Nakaima, Ben Phillips
Lander Trajectory
Altitude versus Range
Altitude (km)
100
50
0
-50
0
200
400
600
Range (km)
Velocity versus Range
800
1000
200
400
600
Range (km)
800
1000
Velocity (km/s)
5
4
3
2
1
0
0
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 77 Dan Nakaima, Ben Phillips
Aeroshell FEM Analysis
Parameter
Maximum value
von Mises stress
2.24  104 N/m2
Displacement
4.62 mm
Compressive stress
2.14  104 N/m2
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 78 Dan Nakaima, Ben Phillips
Heat Shield Analysis
Graphite Ablation
Carbon-Carbon Composite
Honeycomb
Parameter
Value
BC
49.07 kg/m2
Maximum G-loading
5.03 Earth G’s
Estimated cross range
727 km
Material of Each Layer
Thickness
(cm)
Graphite Ablator
0.1
Carbon-Carbon Composite 0.1
Glass Reinforced
10
Polyimide Honeycomb
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 79 Dan Nakaima, Ben Phillips
Retro Rocket Specifics
ΔV
mfinal
tb
Pc
ε
Isp
cF
c*
85 m/s
1575 kg
40 s
3 MPa
30
364 s
1.915
1865 m/s
Lcham
Lnoz
F
Dstop
1739 N
2408 m
Rthroat
Rexit
Rcham
0.0098 m 0.054 m 0.0252 m 0.193 m
0.131 m
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 80 Dan Nakaima, Ben Phillips
Retro Rocket Configuration
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 81 Dan Nakaima, Ben Phillips
Lander Dimensions
Panel
Number
Length (m)
Side A
4
1.3
Side B
4
1.4
Top
1
N/A
Bottom
1
N/A
Height
(m)
Thickness
(cm)
Leg A
Top Panel
Bottom
Panel
Mass (kg)
Leg B
Side Panel A
1.1
2
14.3
1.1
2
15.6
N/A
1
44.5
N/A
10
444.9
Total Mass (kg)
609.0
Leg A
Side Panel B
Leg
Number
Length (m)
Diameter (cm)
Mass (kg)
A
4
0.95
5
14.7
B
8
1.0
5
15.4
Total Mass (kg)
182.0
Leg B
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 82 Dan Nakaima, Ben Phillips
Lander Communication
Lander to Rover
Lander to Transport Vehicle
Frequency
0.42 GHz
Frequency
21.2 GHz
Efficiency Transmitting
0.65
Diameter Receiving
2m
Efficiency Receiving
0.65
Efficiency Transmitting
0.65
Efficiency Receiving
0.65
Bit Error Rate
5.00e-6 bps
Bit Error Rate
5.00e-6 bps
Link Margin
2 dB
Link Margin
2 dB
Noise Temperature
300 K
Noise Temperature
300 K
Atmospheric Loss
2 dB
Atmospheric Loss
2 dB
Distance of Transmission
1 km
Distance of Transmission
229,700 km
Data Rate
2.00e-4 bps
Data Rate
10 Mbps
Diameter Transmitting
0.32 m
Power
0.081 mW
Power
10 W
Mass
0.4 kg
Mass
0.0365 kg
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 83 Dan Nakaima, Ben Phillips
Power Specifics
Lander Power System
Mass of radio-isotope: 60 kg
Mass of batteries for landing: <1 kg
Volume of power systems: 0.2 sq meters
Power produced: 300 W (at beginning of life)
Rover Power System
Mass: 24 kg
Power Produced: 120 W
Volume: ~0.1 sq meters
Failure Rate
Based on previous missions using radio-isotope power sources the failure rate
for both the lander and rover is <1% (no moving parts)
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 84 Dan Nakaima, Ben Phillips
Rover Specifics
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
Mass: approximately 155 kg
Wheelbase (front to rear): 1.2 m
Wheel Size: ~ 0.25 m diameter, 0.15 m width
Track Width: 1.1 m (outside of wheel to outside
of wheel)
Maximum Obstacle Height: 0.30 m rock
Top Deck Height: approx 0.6 m above ground
Rover Body Dimensions: approximately 0.6 x
1.0 x 0.3 m
Mast Instrument Platform Height: 1.0 m above
ground
Arms : 6 degree of freedom (DOF)
One Sol Range: Terrain dependent (50 m
Nominal)
Guidance, Navigation &
Control Sensors: Cameras, LN-200
Effective Stereo Range (Navcams) ~50 m
RPS Power: 200 W continuous (2 RPSs)
Thermal Control: Heat from RPS: Cool from
waste from RPS
Landed Operational Lifetime: 365 Earth Days
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 85 Dan Nakaima, Ben Phillips
Rover Detailed Mass Budget
system
Mobility System
Arm(L)
Arm(R)
Head
Body
component
mass / each
Wheel
2.757
Actuator
0.13
Frame
1.558
Arm
0.65
Motor
0.13
Gripper
0.6
Scoop
0.288
Sensor
0.2
Arm
0.65
Motor
0.13
Raman Spectrometer
4.3
APX
0.8
MI
0.3
Panacam
0.27
Navcam
0.22
Mini-TES
2.1
Motor
0.13
Mast
4.71
Hazcam
0.245
Radiation Detector
5.7
Sample Container
0.213
HGA
5.7
Moror
0.13
UHF Antenna
0.034
(Motor)
0.13
Warm Electronics Box
18
REM
45.9
IMU
0.7
RPS
40
COMM HW
1
#
6
10
2
2
6
1
1
1
2
6
1
1
1
2
2
1
4
1
4
1
1
1
2
1
12
1
1
1
1
1
mass / all
total / system
16.54
20.956
1.3
3.116
1.3
3.168
0.78
0.6
0.288
0.2
1.3
7.48
0.78
4.3
0.8
0.3
0.54
8.31
0.44
2.1
0.52
4.71
0.98
115.214
5.7
0.213
0.867
0.26
0.034
1.56
18
45.9
0.7
40
1
TOTAL
155.128
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 86 Dan Nakaima, Ben Phillips
Rover Communication
Rover to Lander
Frequency
0.41 GHz
Efficiency Transmitting
0.65
Efficiency Receiving
0.65
Mars Rover to Transport Module
Frequency
21.2 GHz
Diameter Receiving
2m
Efficiency Transmitting
0.65
Efficiency Receiving
0.65
Bit Error Rate
5.00e-6 bps
Bit Error Rate
5.00e-6 bps
Link Margin
2 dB
Link Margin
2 dB
Noise Temperature
300 K
Noise Temperature
300 K
Atmospheric Loss
2 dB
Atmospheric Loss
2 dB
Distance of Transmission
1 km
Distance of Transmission
229,700 km
Data Rate
10 Mbps
Data Rate
2.00e-4 bps
Diameter Transmitting
0.32 m
Power
10 W
Mass
0.4 kg
Power
0.22 mW
Mass
0.0374 kg
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 87 Dan Nakaima, Ben Phillips
SRV Specifics
Component
Component
Overall Height
3.02 [m]
Max Radius
0.48 [m]
Tank Height
Radius
Take Off Mass
Component
950 [kg]
Ispvac
344 [s]
Dry Mass
200 [kg]
Mix Ratio
2.99
2.42 [m]
Payload
10 [kg]
Chamber P
300 [psi]
0.48 [m]
Fuel
740 [kg]
Area Ratio
15
Nozzle Length
0.30 [m]
Engines
3
1.707
Exit Radius
0.11 [m]
Thrust/Weight
4.54
Thrust
Coefficie
nt
Throat Radius
0.03 [m]
Total Thrust
16,400 [N]
6064
Cargo Bay Height
0.10 [m]
Burn Time
306 [s]
Characteristic
Velocity
Docking Probe
Length
0.20 [m]
0.20 [m]
Equivalent DV
5.2 [km/s]
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 88 Dan Nakaima, Ben Phillips
Propellant Production Specifics
Methane
Oxygen
Component
Mass
Needed
185 [kg]
Mass
Needed
550 [kg]
Required
Hydrogen
Production
Rate
.616 [kg/day]
Production
Rate
2.46 [kg/day] Production
Equipment
20 [kg]
Time
300 [days]
Time
223 [days]
400 [kw]
Power
Required
47 [kg]
•Reaction
•3CO2 + 6H2 → CH4 + 2CO + 4H2O
•2H2O → 2H2 + O2
•1 kg H2 → 3.98 kg Methane & 7.94 kg O2
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 89 Dan Nakaima, Ben Phillips
Launch Parameters
Parameter
Numeric Value
Altitude [km]
100
Range [km]
732
X-Velocity [km/s]
4.91
Hohmann speed at 100 km [km/s]
4.91
Burn Time [s]
307
Thrust [N]
13,000
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 90 Dan Nakaima, Ben Phillips
Optimal Launch of SRV
• Two-Point Boundary Value
Problem Optimization
x  v x
y  v y
– Used code created by Professor
Williams
Initial Conditions
Final Conditions
to
yf = rc = 100 km
xo
vxf = vc = 4.91 km/s
yo
vyf = 0
vxo
vyo
Spring 2004 AAE450: Slide 91
T
cos( )
m
T
v y  sin(  )  g
m
b  b 2 sin(  )
   b cos( )
v x 
Optimal Launch
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 92 Dan Nakaima, Ben Phillips
Optimal Launch
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 93 Dan Nakaima, Ben Phillips
Optimal Launch
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 94 Dan Nakaima, Ben Phillips
Optimal Launch
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 95 Dan Nakaima, Ben Phillips
SRV Docking Views
Fixed End
Counter Clockwise rotation of 60°
Ayu Abdullah, Masaaki Atsuta, Allison Bahnsen, Franklin Hankins Leigh Janes,
Andy Kacmar, Matt Maier,
Spring 2004 AAE450: Slide 96 Dan Nakaima, Ben Phillips
AMCM
Cost =
β
Ξ
S
(1/(IOC-1900))
φ
D
αQ M δ ε
Bγ
Constants
Variables
α = 5.65e-4
Q = Quantity
β = 0.5941
M = Dry Mass (kg)
Ξ = 0.6604
S = Specification
δ = 80.599
IOC = Initial Operating Capability
ε = 3.8085e-55
B = Block Number
φ = -0.3553
D = Difficulty
γ = 1.5691
Brady Kalb
Spring 2004 AAE450: Slide 97
AMCM Values
Specification
IOC
Block Difficulty
Number
Launch
Vehicle
Transport
1.93
2009
2
-1
2.39
2009
1
0
Lander
2.46
2009
2
-0.5
Rovers
2.14
2009
2
-0.5
Crew Return
Vehicle
2.27
2009
3
-1
Brady Kalb
Spring 2004 AAE450: Slide 98
Cost Schedule
Cost Fraction =
A(10F2 – 20F3 + 10F4) + B(10F3 – 20F4 + 10F5) + 5F4 – 4F5
Where F equals fraction
of project life complete.
For manned mission,
A = 0.32
B = 0.68
Brady Kalb
Spring 2004 AAE450: Slide 99
Inflation Rates
Year
Rate (%)
1999
2.21
2000
3.36
2001
2.85
2002
1.58
2003
2.28
Brady Kalb
Spring 2004 AAE450: Slide 100