An Heritage Approach to Aerospace Risk Based Design: With ...

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PRA-Based EEV Design Changes. Risk-Based Changes to EEV Design • Forebody TPS Carbon-phenolic instead of PICA • Revised magazine/canister/os seal design • Encapsulation/sterilization features of CV (TBD) • Modification of aft body curvature and center of gravity to ensure EEV reorientation (TBD) • Micrometeoroid shield and detector (TBD) • Landing footprint positioning within UTTR 28-29 October 2002 Slide 34 of 42 A Heritage Approach to Aerospace Risk Based Design: With Application Day 1 Afternoon
Phase 7: Hypersonic Entry WAS: • Implemented mitigators – ERV spacecraft packaged in a vault in the shuttle payload bay – Vault will come free of the shuttle during aerodynamic break-up – Vault has sacrificial layer to sustain break-up collisions, and TPS for travel through heat pulse – Vault has a multi-shell design with crushable impact absorbing material and a parachute to descend slowly – Vault will float if free from the shuttle and in water, but is designed to ~6000 m pressure if undamaged • Other potential mitigators – Flotation Device can be added to further assure flotation – “Poison pill” can be added to sterilize samples – Better understanding vault response to hypersonic breakup scenarios IS: • Potential mitigators – Increase shuttle deorbit burn reliability – Implement intervention to recover vault from hostile territory 28-29 October 2002 Slide 35 of 42 A Heritage Approach to Aerospace Risk Based Design: With Application Day 1 Afternoon
Page 1 and 2: An Heritage Approach to Aerospace R
Page 3 and 4: Three Pillars of Good Design • Ma
Page 5 and 6: Make It Safe Design Definition Good
Page 7 and 8: Make It Cost Effective Design Defin
Page 9 and 10: Develop Risk-focused WBS • Trim h
Page 11 and 12: Top Level of Shuttle PRA 1995 Study
Page 13 and 14: Shuttle PRA Restructured for Multis
Page 15 and 16: RLV Loss of Vehicle (LOV) Model (Bi
Page 17 and 18: Shuttle PRA Expanded to Included Cr
Page 19 and 20: STS PRA Generalization Functional
Page 21 and 22: Input Table Parameters From Mission
Page 23 and 24: Potential Impact of Candidate Techn
Page 25 and 26: Earth Entry Vehicle PRELIMINARY wor
Page 27 and 28: OS Configuration Sample Canister Li
Page 29 and 30: Risk-Based Design for Independent F
Page 31 and 32: Risk-based Magazine Concept Lid Mag
Page 33: Detail of Risk-Based Sealing Magazi
Page 37 and 38: Phase 1: Above Safe Orbit • No CN
Page 39 and 40: Impact Velocities The Impact Veloci
Page 41 and 42: Mission Probability of CNA 1.E+00 1

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