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X-ray Calorimeter

X-ray Calorimeter. Systems Engineering Frank Kirchman Theo Bugtong 2 – 6 April, 2012. X-Ray Calorimeter Mission Requirements. X-Ray Calorimeter Mission Requirements (cont.). X-Ray Calorimeter Program flow. Mission Critical Design Review (CDR) 2/13/2019. ATP - Phase B

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X-ray Calorimeter

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  1. X-ray Calorimeter Systems Engineering Frank Kirchman Theo Bugtong 2 – 6 April, 2012

  2. X-Ray Calorimeter Mission Requirements

  3. X-Ray Calorimeter Mission Requirements (cont.)

  4. X-Ray Calorimeter Program flow Mission Critical Design Review (CDR) 2/13/2019 ATP - Phase B Start S/C Bus 9/1/2016 Preliminary Design Review (PDR) 11/22/2017 S/C Bus Contract Award System Definition Review (SDR) Project Start ~ 8/8/2014 Phase A Preliminary Analysis Phase B Definition and Prelim Design Phase C Final Design Preliminary Design Mission Definition System Definition Final Design 16 “months” 24“months” 16“months” End of Extended Mission 6/25/2027 End of Primary Mission 6/25/2025 Instrument Delivery FMA: 12/8/2020 XMS: 2.26/2021 Launch 3/25/2022 Transition To Nominal Ops 6/25/2022 Ready to Ship 10/8/2021 Phase D-1 Subsystem Development, S/C Integration & Test, Launch Prep Phase D-2 Launch & Checkout Total Funded Reserve Phase E/F Operations Fab., S/C Assy & Func. I&T 19mo’s Prep for Launch 3mo’s Obser. I&T 11mo’s Cruise, Orbit Insertion & Checkout PrimaryMission Extended Mission ? 7.5 months Launch (Spread through Phases C & D) 33 “months” 36 months 24 months 3months Notes: Timeline not to scale; 1 “month” = 28 days.

  5. X-Ray Calorimeter System Design Overview • ACS • Internally Redundant Gyro • 4 Head Star Tracker unit with electronics • 4 50Nms 0.2 nm reaction wheels • Absorb 21 days of accumulated CpCg momentum • Avionics • Commercially available IAU • Commercially available support equipment • GPS Heritage Cesium Clock • Communications • Ka-Band for science and ancillary data via DSN 34m • S-Band through TDRSS for critical events • DSN based ranging • Electrical Power • 11Sqm Solar Array(active, unpointed) • 40 AH battery • Flight Dynamics • ΔV requirement is 91m/s • Station Keeping approx every 3 months • DDOR Technique to achieve 3Km accuracy over 21 day arc • Potential modifications to observing plan could extend 21 day arc

  6. X-Ray Calorimeter System Design Overview (cont) • Flight Software • Payload Support • Mechanism Control • Recorder Memory Management • S/C Power System Electronic Support • Health and Safety Management • Mechanical • 8 Sided Gr-Ep S/C structure • Composite honeycomb metering structure • Mission Ops • GSFC MOC • Mission Ops through DSN • Propulsion • Monopropellant Blow Down system • Twelve 4N thrusters • Radiation • 3 year dose is 29 krads (2.5mm shielding) • 5 year dose is 46 krads (2.5mm shielding) • Reliability • Calculated S/C reliability of .9881 after 3 years, .9718 after 5 years • Thermal • FMA Thermally isolated from S/C structure • MLI on S/C, Metering Structure, and solar array reverse • Bus Radiator on anti-sun side

  7. X-Ray Cal Electrical Block Diagram

  8. Observatory Concept

  9. Observatory Concept

  10. X-Ray Calorimeter System Design Overview

  11. X-Ray Calorimeter Data Requirements

  12. X-Ray Calorimeter Power Requirements

  13. Acronyms

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