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Mission Systems Frank Kirchman Ezinne Uzo-Okoro 3 – 7 October, 2011

Advanced X-ray Spectroscopic Imaging Observatory (AXSIO ) NOTE: Original AXSIO info through slide 13, then AXSIO Redux. Mission Systems Frank Kirchman Ezinne Uzo-Okoro 3 – 7 October, 2011. AXSIO Mission Requirements. AXSIO Mission Requirements contd. AXSIO S/C Block Diagram.

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Mission Systems Frank Kirchman Ezinne Uzo-Okoro 3 – 7 October, 2011

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  1. Advanced X-ray Spectroscopic Imaging Observatory(AXSIO)NOTE: Original AXSIO info through slide 13,then AXSIO Redux Mission Systems Frank Kirchman EzinneUzo-Okoro 3 – 7 October, 2011

  2. AXSIO Mission Requirements

  3. AXSIO Mission Requirements contd

  4. AXSIO S/C Block Diagram

  5. AXSIO Program flowrevised from IXO RFI 2 - 8 3 09 Mission Critical Design Review (CDR) 6/11/2018 Phase B Start S/C Bus 12/14/2014 Preliminary Design Review (PDR) 12/12/2016 S/C Bus Contract Award System Definition Review (SDR) Project Start 12/13/2012 Phase A Preliminary Analysis Phase B Definition and Prelim Design Phase C Final Design Preliminary Design Mission Definition System Definition Final Design 24 months 24 months 18 months End of Extended Mission 6/15/2027 Funded Reserve 10/14/2021 Transition To Nominal Ops 7/15/2022 End of Primary Mission 6/15/2025 Instrument Delivery 3/24/2020 Launch 6/15/2022 Phase D-1 Subsystem Development, S/C Integration & Test, Launch Prep Phase E/F Operations Phase D-2 Launch & Checkout Funded Reserve Fab., S/C Assy & Func. I&T ~21 mo.s Prep for Launch ~3 mos Obser. I&T 16 mo.s Cruise, Orbit Insertion & Checkout PrimaryMission Reserve 8mo.s Launch & Checkout Extended Mission 48 months 9 month 1 month 3 mo.s 33 mo.s 24 mo.s Timeline not to scale

  6. AXSIO System Design Overview • Mechanical • 8 Sided Gr-Ep S/C structure surrounding primary mirror • Lower Half Deployable SA to match CP to CG • Thermal • Sunshades to accommodate ±45 Pitch angle • Cold bias baseline with heater control • Propulsion • Mono Prop system for orbit maintenance and momentum unloading • Attitude Control • Star Trackers, Gyros, sun sensors for determination • Momentum wheels for control • Comm • Two DSN S/Ka-Band transponders • Two 10 watt Ka-Band TWTAs • Gimbaled 0.5 M dual frequency high-gain antenna • DSN 34m antenna • Power • SA’s • 28V Bus • Battery

  7. AXSIO System Design Overview • Avionics • Build to print system except for timing system • 100 µsec timing requires custom implementation • Primary C&DH System with Cold Backup system • SW • High heritage reuse • No challenging requirements for AXSIO • I&T • GSFC Facilities Baselined • MSFC XRCF For optical verification • Ops • COTS/GOTS MOC Baselined • Reliability • Class B • Launch Vehicle • Atlas 5 family • Orbital Debris • Micrometeoroid impact assessed • Flight Dynamics • Standard L-2 Halo

  8. AXSIO Observatory Mass

  9. AXSIO Observatory Power

  10. AXSIO Observatory Data Volume

  11. AXSIO Observatory Concept

  12. AXSIO Considerations • Increase Launch Vehicle size • Atlas V 511: ~3,000kg • Atlas V 521: ~3,935kg • Timing aspect requires Ground communications • Modifications to ~2 DSN Stations

  13. Advanced X-ray Spectroscopic Imaging Observatory REDUX(AXSIO) Mission Systems Tony Nicoletti Theo Bugtong 3 – 7 October, 2011

  14. Changes to AXSIO Subsystem Inputs New Design Numbers are in RED

  15. AXSIO Observatory Mass

  16. AXSIO, ReduxLoad Analysis

  17. Data Volume

  18. Data Storage Volume

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