1. 1 Airship fo shizzle

2. Jon Anderson Team Lead Hours Worked: 118 2 Team Member Jon Anderson

3. Agenda 3 Outline: Objective – vehicle selection Design constraints Assumptions General design Equations and Diagrams Performance Deployment Enabling technologies Recommendation and conclusion Questions 3Jon Anderson

4. 4 Objective 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.

5. 5 Objective – Vehicle Selection Mass (lower is better): This category physically rates the aerial vehicles on their expected mass. Technology Development Needs (Lower is better): This category qualitatively rates the aerial vehicles on the amount of research and development needed to make the design option feasible. Operational Risk (Lower is better): This category qualitatively rates the aerial vehicles on the “risk” associated with deploying and operating on Titan. Environmental Tolerance (Higher is better): This category qualitatively rates the aerial vehicles on their ability to withstand the environment and correct faults. Andrew Welsh

6. 6 Objective – Vehicle Selection Surface Capability (Higher is better): This category qualitatively rates the aerial vehicles on their ability to interact with the Titan surface. While all aerial vehicle options can move close to the surface, only the helicopter and combination can physically land on the surface. Mission Completion Probability (Higher is better): This category qualitatively rates the aerial vehicles on their ability to complete the mission Deployment Ability (Higher is better): This category qualitatively rates the aerial vehicles on their deployment methods. Andrew Welsh

7. 7 Objective – Vehicle Selection Jon Anderson CategoryHelicopterAirshipHelicopter & Airship Helicopter & Airship Combination Mass320 kg490 kgUNK kg Technology Development Needs MediumLowerHigh Operational RiskMediumLowMedium Environmental Tolerance MediumHighMedium Surface CapabilityHighMediumHigh Mission Completion Probability Medium High Deployment AbilityMediumHigh Sources: 1. Ravi Prakash. Design of a Long Endurance Titan VTOL Vehicle. Guggenheim School of Aerospace Engineering. 2006 2. Jeffery L Hall. Titan Airship Explorer. JPL. 2002. 3. Dr. Joel S. Levine. Titan Explorer: The Next Step in the Exploration of a Mysterious World. NASA Langley Research Center. 2005

8. 8 Design Constraints Jon Anderson Communication payload Extra redundancy – orbiter and helicopter Science payload Propulsion subsystem Mass assumptions – initial starting value Power subsystem MMRGT

9. 9 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

10. 10 Equations Jon Anderson 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

11. 11 Equations Jon Anderson Drag and Reynolds number equations: Thrust and power available equations:

12. 12 Diagram of Airship Jon Anderson

13. 13 Reynolds # and Drag vs Velocity Jon Anderson

14. 14 Power Required/Available vs Velocity Jon Anderson

15. 15 Inflation time/percent vs Lift Jon Anderson

16. 16 Performance Jon Anderson Mass195 Kg Operational Cruse Velocity2.5 m/s Max Velocity2.98 m/s Min Climb/Descent Rate *50 m/min Range36200 km Service Ceiling5 km Absolute Ceiling40 km Estimated Lifetime *150 days

17. 17 Deployment Jon Anderson Airship inflation immediate Both bayonets and main envelope Changing ballistic coefficient Separate via explosive shearing bolts Immediately max velocity

18. 18 Enabling Technologies Jon Anderson Multi Mission Radioisotope Thermal Generator Heat exchanger – not fins Centrifugal turbine – low power/mass flow levels Alternator – bearing system, no gears Centrifugal Compressor 5 fold increase in power Lower mass

19. 19 Recommendation and Conclusion Jon Anderson High Altitude Design Detailed data bandwidth analysis Hull/system optimization Experments

20. 20 Questions? Jon Anderson

21. 21 Backup slides - Mass Jon Anderson ComponentMass (kg)Mass after 20% Margin (kg) Subsystem Power2nd Generation MMRTG1720.4 Battery - 12 A h lithium0.470.564 Turbomachinery3.944.728 Turbine0.91.08 Compressor0.91.08 Piping0.7160.8592 Electric Motor1.081.296 Alternator1.081.296 Total26.08631.3032 PropulsionPropeller, axel, case*5.256.3 Total5.256.3 Science InstrumentsHaze and Cloud Partical Detector33.6 Mass Spectrometer1012 Panchromatic Visible Light Imager1.31.56 Total14.317.16 CommunicationX-Band Omni - LGA0.1140.1368 SDST X-up/X-down2.73.24 X-Band TWTA2.12.52 UHF Transceiver (2)9.811.76 UHF Omni1.51.8 UHF Diplexer (2)11.2 Additional Hardware (switches, cables, etc.)67.2 Total23.21427.8568 ACDSSun Sensors0.91.08 IMU (2)910.8 Radar Altimeter4.45.28 Antennas for Radar Altimeter0.320.384 Absorber for Radar Altimeter0.380.456 Air Data System with pressure and temperature56 Total2024

22. 22 Backup slides - Mass Jon Anderson C&DHFlight Processor0.60.72 Digital I/O - CAPI Board0.60.72 State of Health and Attitude Control0.60.72 Power Distribution (2)1.21.44 Power Control0.60.72 Mother Board0.80.96 Power Converters (For Integrated Avionics Unit)0.80.96 Chassis3.44.08 Solid State Data Recorder1.61.92 Total10.212.24 StructureAirship Hull4.575.484 Gondola*8.410.08 Tail Section: 4 Fins and attachments*8.410.08 Attitude Control44.8 Helium Mass (Float at 5 km)29.9535.94 Inflation tank for Helium*19.1723.004 Bayonet fans and eqipment5.56.6 Total79.9995.988 ThermalInflight and during operation8.279.924 Total8.279.924 Total Airship Dry Mass187.31224.772 Total Aiship Float Mass217.26260.712

23. 23 Backup slides Component Power Required (W) Power Required after 20% Margin (W) Subsystem Power580 W Generated ProplusionPropeller/EngineSee Figure 2 TotalSee Figure 2 BayonetsFans (2)90108 Total90108 Science InstrumentsHaze and Cloud Partical Detector20 Mass Spectrometer28 Panchromatic Visible Light Imager10 Total5869.6 CommunicationUHF Transceiver74.88 Total74.889.76

24. 24 Backup slides - Power Jon Anderson ACDS*Sun Sensors 0.56 IMU22.2 Radar Altimeter37.6 Air Data System with pressure and temperature7.72 Total68.08 C&DH*Flight Processor; >200 MIPS, AD750, cPCI11.6 Digital I/O - CAPI Board3.44 State of Health and Attitude Control - SMACI3.44 Power Distribution6.88 Power Control3.44 Power Converters (For Integrated Avionics Unit)13.84 Solid State Data Recorder0.64 Total43.28 Total Power Required without proplusion with all systems operating - Straight and level244.16 Total Power Available for Propulsion - Straight and level335.84