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Airship fo shizzle

Airship fo shizzle. Team Member. Jon Anderson Team Member Hours Worked: 118. Agenda. Outline: Vehicle selection – Military Decision Making Process [6] Airship Design/Performance Enabling technologies Recommendation and conclusion Questions. 3. Problem.

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Airship fo shizzle

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  1. Airship fo shizzle

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

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

  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 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 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. Jon Anderson

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

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

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

  17. Diagram of Airship • 20% Margins • Ballonet, fins, and gondola approx. Jon Anderson

  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

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

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

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

  25. References • Wolfram: The Mathematica Book, Wolfram Media, Inc., Fourth Edition, 1999 • Gradshteyn/Ryzhik: Table of Integrals, Series and Products, Academic Press, Second Printing, 1981 • Wright, Henry S. Design of a Long Endurance Titan VTOL Vehicle. Georgia Institute of Technology. • Levine.S.J. NASA Space Science Vision Missions - Titan Explorer. AIAA Inc. • Hall. L. J. Titan Airship Explorer. IEEE Aerospace. 2001. • FM 101-5. Staff Organization and Operation.

  26. Questions? Jon Anderson

  27. Backup slides - Mass Jon Anderson

  28. Backup slides - Mass Jon Anderson

  29. Backup slides - Power

  30. Backup slides - Power Jon Anderson

  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

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