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Airship fo shizzle

Jon AndersonTeam Member

Hours Worked: 118

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Team Member

Jon Anderson

Agenda

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Outline:• Vehicle selection – Military Decision Making Process [6]

• Airship Design/Performance

• Enabling technologies

• Recommendation and conclusion

• Questions3Jon Anderson

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Problem

• Determine which aero-vehicle or combination of aero-vehicles would be best suited for a mission to Titan.

• General goals from project• specific goals (facts) stemmed from project goals

• Apply Military Decision Making Process

• Present short version

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Recommendation

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Facts/Assumptions

Facts: • Vehicle(s) must be aero-vehicles.• Vehicle(s) must be able to land.• Vehicle(s) must be able to carry the given science instrument payload.• Vehicle(s) must have some means of self propulsion.

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• All designs will have some means to communicate to the orbiter or earth

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Courses of Action

• Helicopter

• Airship

• Tilt-Rotor

• Fixed wing aircraft

• Any combination of the above vehicles

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Screening Criteria

• Vehicles must have some basic research done from other sources.

• NASA - Airship [3]• IEEE (Institute of Electrical and Electronics Engineers) – Airship [5]• Georgia Tech - Helicopter [6]

• Detailed design out of scope of project

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Analysis – COA screened out

After research we screened out:

• Tilt rotor

• Airplane/Glider

• Any combination with these two options.

• Ex. Airplane - airship, tilt rotor – airplane

More time – further design options

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Evaluation/Weighing Criteria

• Mass – Lower is better – 10%

• Pre Designed Level – Higher is better – 10%

• Operational Life time – Longer is better – 15%

• Top Speed – Higher is better – 15%

• Redundancy – 1 if not available, 0 if available – 50%

• Assign 1,2,or 3 with 1 being the best in that category

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Information Presentation

• Took all COA

• Applied screening, evaluation, weighing criteria

• Assigned number values based on 1 as the “best” and 3 being the “worst”

• Tallied findings in a table – lowest score = the best option

Example calculation for combination vehicle findings:

• 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

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 vehicle design 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 earth

• Science payload• Reduced

• Power subsystem• New Power systems – more power less 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 [3][5]:

Shape and Surface Area equations [1][2]:

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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 [3]:

Thrust and power available equations [5]:

fowardrequired DUPower

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Diagram of Airship

Jon Anderson

Length 13.83 m

Width 3.45 mVolume 34.47 mBallonet volume* 8.96 m

Fins* 1x1x.7 m

Gondola* .7x.7x1.63 m

• 20% Margins

• Ballonet, fins, and gondola approx.

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3

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Reynolds # and Drag vs Velocity

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Power Required/Available vs Velocity

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Inflation time/percent vs Lift

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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 ballonets and main envelope

• Changing ballistic coefficient

• Separate via explosive shearing bolts • Immediately max velocity

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Enabling Technologies

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Multi Mission Radioisotope Thermal Generator

• Complicated – beyond scope of design

• 5 fold increase in power• Lower mass

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Recommendation and Conclusion

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High Altitude Design

Detailed data bandwidth analysis

Hull/system optimization

Experiments

Fixed wing – tilt rotor design

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1. Wolfram: The Mathematica Book, Wolfram Media, Inc., Fourth Edition, 1999

2. Gradshteyn/Ryzhik: Table of Integrals, Series and Products,

Academic Press, Second Printing, 1981

3. Wright, Henry S. Design of a Long Endurance Titan VTOL Vehicle. Georgia Institute of Technology.

4. Levine.S.J. NASA Space Science Vision Missions - Titan Explorer. AIAA Inc.

5. Hall. L. J. Titan Airship Explorer. IEEE Aerospace. 2001. 6. FM 101-5. Staff Organization and Operation.

References

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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 - Power

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

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Backup slide: 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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Backup Slide: 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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Backup Slide: COA - Combination

Mass – UNK – Assume largest

Pre Designed Level – Medium

Operational Life time – 120 Days

Top Speed – 3.5 m/s

Redundancy - Yes