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X-Ray Calorimeter Study

X-Ray Calorimeter Study. Mission Operations Jeffrey Ferrara 2 – 6 April, 2012. Topics. Mission Operations Summary Ground System Functional Architecture MOC Architecture (typical) Study Requirements – Mission Operations Key Customer Requirements Mission Overview Mission Timeline

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X-Ray Calorimeter Study

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  1. X-Ray Calorimeter Study Mission Operations Jeffrey Ferrara 2 – 6 April, 2012

  2. Topics • Mission Operations Summary • Ground System Functional Architecture • MOC Architecture (typical) • Study Requirements – Mission Operations • Key Customer Requirements • Mission Overview • Mission Timeline • Technology Assessment • Cost Basis of Estimate • Mission Operations Periods • Staffing Periods Used for Costing • Cost Summary • Risk/Issues/Concerns • Additional Trades • Acronyms

  3. Mission Operations Summary • Mission Operation Control (MOC): • Provides “standard” set of functional components to support Mission Operations (e.g., S/C commanding, mission planning/scheduling, and RT TLM monitoring, HK trending and analysis). • Provides level zero processing (LZP) • Level 0 Products: Time-ordered, quality annotated data sets produced for each contact • Level 0 products transferred to Science Operations Center (SOC) • Provides voice communications between the MOC & SOC for coordination • Space-Ground contact profile • DSN (34 meter antenna) • TDRSS for launch & early mission operations • Data rates: Science: 72 Kbps nominal, 1.8 Mbps peak, Housekeeping: 4.1 Kbps • Spacecraft data link rates: • DSN • S-band via HGA • 2 kbps command • 8 kbps housekeeping telemetry • S-band via Omni • 1 kbps command • 2 kbps housekeeping telemetry • Ka-band • 20 Mbps science telemetry • TDRSS • 1 kbps command • 1 kbps telemetry • Data Latency Requirements: • 72 hour required • Data Recovery: • Assume 98% recovery requirement (end-to-end) • Orbit Determination via DSN ranging • SDPC & SOC costs to be defined by the customer; FDF costs covered by FDF discipline engineer

  4. Ground System Functional Architecture Legend: CMD = Commanding HK = House-Keeping data TLM = Telemetry data Launch & early mission S-band TLM: 1 kbps CMD: 1 kbps Ka-band TLM: 20 Mbps S-band TLM: 8 kbps CMD: 2 kbps Mission Ops Center Mission planning & scheduling Orbit determination/control Network & contact scheduling Commanding S/C monitor/control RT health/safety processing Trending/Analysis Instrument data handling Level 0 product processing Level 0 Data Archive FDF is costed by FDF engineer Science Ops Center Data Processing & Analysis Experiment planning Payload monitoring Costed by customer Science Data Processing Center (SAO) Data Processing Costed by customer Voice TLM, HK DSN WSC TLM, HK 1.5 Mbps CMD TLM, HK 1.5 Mbps CMD Basis of cost study is in red

  5. MOC Architecture (typical) Level Zero Processing Attitude Control Flight Dynamics Telemetry & Command Data Front-end System Ground Stations SDPC LAN/Message Bus Mission File Server /Archive Anomaly Notification Event Display/ Logging Data Analysis & Trending Mission Planning & Scheduling Email & Internet Access Internet

  6. Key Customer Requirements • Launch date: 3/25/2022 • Mission Life: 3yrs. required, 5 yrs. desired • SE L2 solar orbit (with ~800,000 x ~500,000 km halo) with no eclipses • Class B mission

  7. Mission Overview • X-ray telescope with 1 instrument, the X-ray Micro-calorimeter Spectrometer (XMS) SA & HGA View Target Side View Top View Sun

  8. Mission Overview Launch (L) at T0 Transfer Trajectory Insertion (TTI) at L + 25 to 120 minutes After outgassing Jettison/Open Flight Mirror Assembly Covers, Turn cryo on (TTI+21 days) Open instrument covers, Gate valves LV Separation: TTI + 5 minutes Calibrate w/ Celestial Targets then start Science Ops Deploy Solar Arrays & High Gain Antenna ELV Dispersion Corrections at TTI + 24 hours Commence Instrument Aliveness Checks EOM/Disposal: L + 3-5 years First Mid-Course Correction: TTI + 16 days Spacecraft full power on Instrument internal background measurements Commence Observatory Checkout Establish power positive attitude Second Mid-Course Correction: TTI + 60 days Arrive L2, continue with Science Ops L2 Orbit Insertion (L2OI) TTI + 100 days Instrument cool down complete, Commence cold checks TTI + 71 days Launch (L) at T0

  9. Typical Ops Day • Two – three separate observations per day • One slew per observation (~ 60 minutes) • Observations up to 100K sec each (typical = 50K sec) • Coincident with one of the slews, one 2-hr cryogenic cooler regeneration per day • One data downlink per day • Data received by MOC processed to L-0 • L-0 data received by SDPC processed to L-1 through L-3 products • L-1 through L-3 products received by the SOC distributed to PIs and analyzed. Slew = Observation = Regeneration = Downlink = Data Processed = Typical 24 hours

  10. Mission Timeline Launch 6/11/2021 L2 Insertion Disposal Prime Mission 36 - 60 months Mission Closeout Cruise 100 days • Instrument Aliveness Checks • Begin Operations

  11. Technology Assessment • Use COTS/GOTS S/W & H/W as basis for MOC implementation • Software packages are available to satisfy MOC required functionality: • ITOS, ASIST, EPOCH 2000, ALTAIR are commercially available today and provide required functionality for Spacecraft Command/Control and Level Zero (LZ) Processing. • Standard PC’s typically with Linux as OS • Low data volume so no special/new technology required • Most required technologies have been at least demonstrated; many in currently operational systems. • Technology Complexity: Low • Technology Readiness Level: 9

  12. Cost Basis of Estimate • All costs are ROM estimates • Goddardestimated FY2012 Cost Rates used (FY2010 + 4%) • More detail available in the Costs Spreadsheet • Development Cost Assumptions • For MOC planning/scheduling, command load generation/validation and data processing support • Provides three physical h/w strings (primary, backup & test) • Most MOC functions are provided by COTS and/or GOTS software • Minimal new development for Mission unique requirements. • Operations Staffing Cost Assumptions • 8 x 7 operations • Communications Link Cost Assumptions • DSN • TDRSS for launch & early mission • Daily downlinks (8 - 33 minutes, depends on high rate observation time) • T1 links between ground elements (1.544 Mbps) • Level 0 Processing • Data available near real time • NOTE: FDF costs are provided by the FDF engineer; SDPC &SOC costs are provided by the customer

  13. Mission Operations Periods Period 4 (2 months) Period 5 (35-59 months) Preliminary Design Final Design Mission Cleanup Bus & P/L Fab/Assy/Test Payload Primary + Extended Ops Bus & P/L I&T System Definition Prep for Launch Launch & Checkout Phase B Start 9/1/2016 CDR 2/13/2019 PDR 11/22/2017 Project Start 8/8/2014 Phase C Design Phase B Definition Phase A Preliminary Analysis Period 1 (24 months) Mission Definition 16 months 24 months 16 months Period 3 (9 months) Period 2 (25.5 months) Period 6 (3 months) Launch 3/25/2022 Disposal 6/25/2027 Phase D-1 Subsystem Development and Spacecraft Integration and Test Funded Schedule Reserve 7.5 mo. Phase E/F Operations Phase D-2 Launch & Checkout Period 5-1 (1 month) 19 mo 11 mo 3 mo 3 month 62 months 33 months

  14. Staffing Periods Used for Costing

  15. Cost Summary (ROM)

  16. Risk/Issues/Concerns • Risks • If the ACS fails such that the Solar Array is not shielding the FMA, then only a small attitude change could endanger the FMA (i.e., cause it to point sunward). Under the right circumstances there would be little time for the FOT to react to the situation before FMA failure. Could mitigate with FMA cover for safehold or additional sun shade. • Issues • none • Concerns/Recommendation • Due to the highly variable data rates and length of observations it is very important to track the data volume generated as part of the science planning activity

  17. Additional Trades • Consider reducing staffed hrs. to 8x5 • Consider a multi-mission MOC

  18. Acronyms CDR Critical Design Review CMD Command COTS Commercial Orbital Transportation Services or Commercial Off the Shelf DSN Deep Space Network EOM End of Mission ES L2 Earth – Sun Lagrange Point FT Functional Test GOTS Government Off the Shelf HGA High Gain Antenna HK Housekeeping Kbps Kilo-bits per second LV Launch Vehicle LZP Level Zero Processing Mbps Mega-bits per second MOC Mission Operations Center RT Real Time SA Solar Array S/C Spacecraft SOC Science Operations Center TDRSS Tracking & Data Relay Satellite System TLM Telemetry ITOS, ASIST, EPOCH 2000, ALTAIR are COTS/GOTS available software packages for controlling spacecraft & performing level zero processing

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