1. ROVER EGRESS DESIGN PROGRESS REPORT 9/26/2011 Anton Galkin Zack Morrison Hahna Alexander 1

2. Progress Report  Semester Schedule  Research of Design Constraints  Initial Design Concepts  Comparison of Designs  Selected Design Path  Test Plan 2

3. Semester Schedule 3

4. Research: Launch Dynamics Static Loads:  +6G/–2G axial  ±2G lateral Dynamic loads:  MIN: 20G at 100Hz  MAX: 3000G at 2000Hz Vibration:  Fundamental vibration modes do not couple with Falcon 9 rocket  Precision components held in place by friction can become misaligned Center of Gravity Lateral Offset:  MAX 0.5in spin-stabilized mission  MAX 5.0in non-spin stabilized 4

5. Research: Vacuum Space Flight Thermal regulation through radiation only High voltage charge can accumulate on spacecraft  Voltage potential over non-conducting (e.g. composite) surfaces  Uncontrolled discharge can damage spacecraft Ultraviolet radiation detrimental to many materials  Polymer erosion & out-gassing can contaminate spacecraft  Stripping of oxidation layer can cause cold welding 5

6. Temperature Variation 6

7. Material Selection  Aluminum  Titanium  Composite (carbon fiber & aluminum honeycomb) 7

8. Design Concepts 8

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11. Design Concepts 11

12. Design Concepts 12

13. Design Comparison Chart 1. Dual Direction Ramp 2. Segmented Ramp 13

14. Comparison to Segmented Design 14

15. Test Plan – Deployment  Deployment Reliability  Successful Deployment  Landing Accuracy  Deployment Time  Geometric Constraints  Deployment Angle  Stress/Deflection  Component Failure  Impact Force 15

16. Test Plan – Egress  Egress Reliability  Egress Success  Stress/Deflection  Joint Failure  Wheel-Ramp Interaction 16

17. Test Plan – Landing Conditions  Lander Tilt – Deployment Reliability  Lunar Terrain – Deployment, Egress Reliability  Worst Case 30cm Rocks/Holes Ground-Hole Ground-Rock Rock-Rock Hole-Hole Rock-Hole 17

18. Questions? 18