1 Airship fo shizzle

Jon Anderson Team Member Hours Worked: Team Member Jon Anderson

Agenda 3 Outline: Vehicle selection – Military Decision Making Process [6] Airship Design/Performance Enabling technologies Recommendation and conclusion Questions 3Jon Anderson

4 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

5 Recommendation A combination helicopter – airship design Helicopter – Primary science mission Collect scientific information Airship – Primary communication mission Relay science information to orbiter/earth

6 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

7 Courses of Action Helicopter Airship Tilt-Rotor Fixed wing aircraft Any combination of the above vehicles

8 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

9 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

10 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

11 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

12 Analysis Continued Mass (10%) Pre-design level (10%) Life time (15%) Speed (15%) Redun. (50%) Total Airship Helicopter Combination 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.

13 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.

14 Design Constraints Jon Anderson Communication payload Extra redundancy – orbiter and earth Science payload Reduced Power subsystem New Power systems – more power less mass.

15 Equations Jon Anderson Buoyancy and Volume equations [3][5]: Shape and Surface Area equations [1][2]:

16 Equations Jon Anderson Drag and Reynolds number equations [3]: Thrust and power available equations [5]:

17 Diagram of Airship Jon Anderson Length13.83 m Width3.45 m Volume34.47 m Ballonet volume*8.96 m Fins*1x1x.7 m Gondola*.7x.7x1.63 m 20% Margins Ballonet, fins, and gondola approx.

18 Reynolds # and Drag vs Velocity Jon Anderson

19 Power Required/Available vs Velocity Jon Anderson

20 Inflation time/percent vs Lift Jon Anderson

21 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

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

23 Enabling Technologies Jon Anderson Multi Mission Radioisotope Thermal Generator Complicated – beyond scope of design 5 fold increase in power Lower mass

24 Recommendation and Conclusion Jon Anderson High Altitude Design Detailed data bandwidth analysis Hull/system optimization Experiments Fixed wing – tilt rotor design

25 1.Wolfram: The Mathematica Book, Wolfram Media, Inc., Fourth Edition, Gradshteyn/Ryzhik: Table of Integrals, Series and Products, Academic Press, Second Printing, 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 FM Staff Organization and Operation. References

26 Questions? Jon Anderson

27 Backup slides - Mass Jon Anderson ComponentMass (kg)Mass after 20% Margin (kg) Subsystem Power2nd Generation MMRTG Battery - 12 A h lithium Turbomachinery Turbine Compressor Piping Electric Motor Alternator Total PropulsionPropeller, axel, case* Total Science InstrumentsHaze and Cloud Partical Detector33.6 Mass Spectrometer1012 Panchromatic Visible Light Imager Total CommunicationX-Band Omni - LGA SDST X-up/X-down X-Band TWTA UHF Transceiver (2) UHF Omni UHF Diplexer (2)11.2 Additional Hardware (switches, cables, etc.)67.2 Total ACDSSun Sensors IMU (2)910.8 Radar Altimeter Antennas for Radar Altimeter Absorber for Radar Altimeter Air Data System with pressure and temperature56 Total2024

28 Backup slides - Mass Jon Anderson C&DHFlight Processor Digital I/O - CAPI Board State of Health and Attitude Control Power Distribution (2) Power Control Mother Board Power Converters (For Integrated Avionics Unit) Chassis Solid State Data Recorder Total StructureAirship Hull Gondola* Tail Section: 4 Fins and attachments* Attitude Control44.8 Helium Mass (Float at 5 km) Inflation tank for Helium* Bayonet fans and eqipment Total ThermalInflight and during operation Total Total Airship Dry Mass Total Aiship Float Mass

29 Backup slides - Power 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 Total CommunicationUHF Transceiver74.88 Total

30 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 level Total Power Available for Propulsion - Straight and level335.84

31 Backup slide: COA - Airship Mass – 490 kg Pre Designed Level - High Operational Life time – 150 Days Top Speed – 3.5 m/s Redundancy - None

32 Backup Slide: COA - Helicopter Mass – 290 kg Pre Designed Level - low Operational Life time – 120 Days Top Speed – 4.5 m/s Redundancy - None

33 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