1 airship fo shizzle. jon anderson team lead hours worked: 118 2 team member jon anderson
TRANSCRIPT
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Airship fo shizzle
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Jon AndersonTeam Lead
Hours Worked: 118
2
Team Member
Jon Anderson
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Agenda
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Outline:• Vehicle selection – Military Decision Making Process (FM 101-5)• Airship Design• Airship Performance• Deployment• Enabling technologies• Recommendation and conclusion• Questions
3Jon Anderson
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Problem
• Determine which aero-vehicle or combination of aero-vehicle would be best suited for a mission to Titan.
• Apply Military Decision Making Process
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Recommendation
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Facts
• Vehicle must be able to land.• Vehicle must be able to carry the given science instrument payload.• Vehicle must have some means of self propulsion.• Only a helicopter-airship combination will be evaluated.
• Most heavily researched options.
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Assumptions
• All designs can survive atmospheric conditions• All designs can be packaged into a 3 m diameter aero shell• All designs will operate within 0-5 km of the surface
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Courses of Action
Helicopter
Airship
Tilt-Rotor
Airplane/Glider
Helicopter/Airship combination
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Screening Criteria
• Vehicles must have some basic research done from other sources.• Can’t design vehicles from nothing
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Evaluation Criteria
Mass – Lower is better
Pre Designed Level – Higher is better
Operational Life time – Longer is better
Top Speed – Higher is better
Redundancy – 0 if not available, 1 if available
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Weighing Criteria
Pre-designed Level – 10%
Mass – 25%
Operational Life time – 15%
Top Speed – 10%
Redundancy – 40%
Assign 1,2,or 3 with 1 being the best in that category
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Analysis – COA screened out
Tilt rotor
Airplane/Glider
Lack of information
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COA - Airship
Mass – 490 kg
Pre Designed Level - High
Operational Life time – 150 Days
Top Speed – 3.5 m/s
Redundancy - None
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COA - Helicopter
Mass – 290 kg
Pre Designed Level - low
Operational Life time – 120 Days
Top Speed – 4.5 m/s
Redundancy - None
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COA - Combination
Mass – UNK – Assume largest
Pre Designed Level – Medium
Operational Life time – 120 Days
Top Speed – 3.5 m/s
Redundancy - Yes
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Information Presentation
Took COA
Applied weighing criteria
Assigned number values based on 1 as the “best” and 3 being the “worst”
Tallied findings in a table
Example calculation for combination values:• Mass - highest mass – scored 3, weight 10%, score = .3• Pre-design level – second highest – scored 2, weight 10%, score = .2
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Analysis Continued - Airship
Mass (10%)
Pre-design level (10%)
Life time (15%)
Speed (15%)
Redun. (50%)
Total
Airship .20 .1 .15 .30 .5 1.25
Helicopter .10 .3 .3 .15 .5 1.35
Combination
.30 .2 .3 .30 0 1.10
Overall Total score – Lower is better
Combination is the recommended COA
Through research – divided mission of science and communication to save on overall mass.
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Airship Design
Jon Anderson
Mission Goal: The primary mission of the airship is to function as a relay between the orbiter and the helicopter. The secondary mission of the airship is to function as a reserve platform capable of carrying out the science mission should the helicopter become inoperable.
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Design Constraints
Jon Anderson
• Communication payload• Extra redundancy – orbiter and helicopter
• Science payload
• Power subsystem• MMRGT
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Assumptions
Jon Anderson
Mass Assumption:
• Needed initial estimate for mass of hull and structural components
• Found fraction of weight for non-hull components vs NASA• Estimated initial weight
• Designed airship, calculated final mass
• Reiterated process with calculated mass
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Equations
Jon Anderson
Vm
TR
Mp
VgB
atm
atmHe
AirshiptianHeatm
)(
2
2
1
22
222
2
1
cos
56
10312
1:4,3
4
ab
ab
r
rb
bbabrbS
abV
Buoyancy and Volume equations:
Shape and Surface Area equations:
Sources:5. Wolfram: The Mathematica Book, Wolfram Media, Inc., Fourth Edition, 1999 6. Gradshteyn/Ryzhik: Table of Integrals, Series and Products, Academic Press, Second Printing, 1981
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Equations
Jon Anderson
)2(2
1
302.1252.172.
,3/22
6/1
2.13/1
,
bVR
CVUD
R
ld
ld
dl
C
e
HullDVHull
e
HullDV
Drag and Reynolds number equations:
Thrust and power available equations:
fowardrequired DUPower
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Diagram of Airship
Jon Anderson
Length 13.83 m
Width 3.45 mVolume 34.47 m^3Ballonet volume 8.96 m^3
Fins 1x1x.7 m
Gondola .7x.7x1.63 m
20% Margins
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Reynolds # and Drag vs Velocity
Jon Anderson
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Power Required/Available vs Velocity
Jon Anderson
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Inflation time/percent vs Lift
Jon Anderson
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Performance
Jon Anderson
Mass 195 Kg
Operational Cruse Velocity 2.5 m/s
Max Velocity 2.98 m/s
Min Climb/Descent Rate * 50 m/min
Range 36200 km
Service Ceiling 5 km
Absolute Ceiling 40 km
Estimated Lifetime * 150 days
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Deployment
Jon Anderson
Airship inflation immediate
• Both bayonets and main envelope
• Changing ballistic coefficient
• Separate via explosive shearing bolts • Immediately max velocity
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Enabling Technologies
Jon Anderson
Multi Mission Radioisotope Thermal Generator
• Complicated – beyond scope of design
• 5 fold increase in power• Lower mass
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Recommendation and Conclusion
Jon Anderson
High Altitude Design
Detailed data bandwidth analysis
Hull/system optimization
Experments
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Questions?
Jon Anderson
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Backup slides - Mass
Jon Anderson
Component Mass (kg) Mass after 20% Margin (kg)Subsystem
Power 2nd Generation MMRTG 17 20.4Battery - 12 A h lithium 0.47 0.564Turbomachinery 3.94 4.728Turbine 0.9 1.08Compressor 0.9 1.08Piping 0.716 0.8592Electric Motor 1.08 1.296Alternator 1.08 1.296
Total 26.086 31.3032
Propulsion Propeller, axel, case* 5.25 6.3
Total 5.25 6.3
Science Instruments Haze and Cloud Partical Detector 3 3.6Mass Spectrometer 10 12Panchromatic Visible Light Imager 1.3 1.56
Total 14.3 17.16
Communication X-Band Omni - LGA 0.114 0.1368SDST X-up/X-down 2.7 3.24X-Band TWTA 2.1 2.52UHF Transceiver (2) 9.8 11.76UHF Omni 1.5 1.8UHF Diplexer (2) 1 1.2Additional Hardware (switches, cables, etc.) 6 7.2
Total 23.214 27.8568
ACDS Sun Sensors 0.9 1.08IMU (2) 9 10.8Radar Altimeter 4.4 5.28Antennas for Radar Altimeter 0.32 0.384Absorber for Radar Altimeter 0.38 0.456Air Data System with pressure and temperature 5 6
Total 20 24
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Backup slides - Mass
Jon Anderson
C&DH Flight Processor 0.6 0.72
Digital I/O - CAPI Board 0.6 0.72
State of Health and Attitude Control 0.6 0.72
Power Distribution (2) 1.2 1.44
Power Control 0.6 0.72
Mother Board 0.8 0.96
Power Converters (For Integrated Avionics Unit) 0.8 0.96
Chassis 3.4 4.08
Solid State Data Recorder 1.6 1.92
Total 10.2 12.24
Structure Airship Hull 4.57 5.484
Gondola* 8.4 10.08
Tail Section: 4 Fins and attachments* 8.4 10.08
Attitude Control 4 4.8
Helium Mass (Float at 5 km) 29.95 35.94
Inflation tank for Helium* 19.17 23.004
Bayonet fans and eqipment 5.5 6.6
Total 79.99 95.988
Thermal Inflight and during operation 8.27 9.924
Total 8.27 9.924
Total Airship Dry Mass 187.31 224.772
Total Aiship Float Mass 217.26 260.712
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Backup slides
ComponentPower Required (W)
Power Required after 20% Margin (W)
Subsystem
Power 580 W Generated
Proplusion Propeller/Engine See Figure 2 See Figure 2
Total See Figure 2 See Figure 2
Bayonets Fans (2) 90 108
Total 90 108
Science Instruments Haze and Cloud Partical Detector 20
Mass Spectrometer 28Panchromatic Visible Light Imager 10
Total 58 69.6
Communication UHF Transceiver 74.88
Total 74.8 89.76
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Backup slides - Power
Jon Anderson
ACDS* Sun Sensors 0.56IMU 22.2Radar Altimeter 37.6Air Data System with pressure and temperature 7.72
Total 68.08
C&DH* Flight Processor; >200 MIPS, AD750, cPCI 11.6Digital I/O - CAPI Board 3.44State of Health and Attitude Control - SMACI 3.44Power Distribution 6.88Power Control 3.44Power Converters (For Integrated Avionics Unit) 13.84Solid State Data Recorder 0.64
Total 43.28
Total Power Required without proplusion with all systems operating - Straight and level 244.16
Total Power Available for Propulsion - Straight and level 335.84