FORMOSAT-7/COSMIC-2 Overview Vicky Chu, Jer Ling, Tom Lin, Joe Fong, Feng-Tai Huang, Guey-Shin Chang April 15, 2011
Program Status AIT-TECRO Agreement on FORMOSAT-7/COSMIC-2 joint program has been signed in May, 2010. Joint Program Mission Design Review has been completed in August, 2010. Joint Program System Requirement Review has been completed in April 2011.
Joint Mission Between NSPO and NOAA Both NSPO NOAA
Users Requirements
Data Types and Data Products Data Products Neutral Atmosphere (1 km~ 60 km) Ionosphere and Space Weather (90 km ~700 km) Bending angle profile Refractivity profile Temperature profile Water vapor profile Total Electron Content Electron density profile Scintillation amplitude index Scintillation phase index Metadata GNSS and LEO satellite orbit location files Excess phase files Occultation tables Records of major processing algorithm revisions
Data Requirements for Neutral Atmosphere Product Item Threshold Objective Number of Profiles per day Corresponding avg. #/location/day 8000 4 10000 5 Average Latency [minutes] 45 [TBR] 15 Average Revisit Time [hours] 6 4.8
Spatial and Temporal Resolution Spatial resolution Horizontal: Near-uniform global data coverage (data density at any location on the Earth s surface varies by less than a factor of 2 relative to any other location) Vertical: 0.1 km at altitudes < 25 km; 1 km at altitudes 25-60 km Temporal resolution Full diurnal sampling (the local time gaps are less than 5 hours at any latitude in any given day)
Quality Control Neutral Atmosphere Threshold Objective 70% 90% Ionosphere 75% 90% Region Refractivity and Bending Angle Outside 30 Latitude Within 30 Latitude Outside 30 Latitude Within 30 Latitude 85% 65% 90% 70%
Key Requirements (1/2) Data Profiles 8000+ per day (FORMOSAT-3 Reference: 1800-2200 points per day) Data Latency 45 minutes [TBR] (FORMOSAT-3 Reference: 86 % of data is within 3-hr latency) Data Distribution Geophysical homogeneously distributed Full diurnal sampling (FORMOSAT-3 Reference: Geophysical homogeneously distributed)
Key Requirements (2/2) System Operational Availability 95% [TBR] Mission duration 5 years beyond 2nd launch [TBD] (FORMOSAT-3 Reference: 2 years) Satellites life (1st launch) 2015 2020 Satellites life (2nd launch) 2017 2022 Mission Duration
Mission Requirements
Mission Baseline FORMOSAT-7 First Launch Second Launch Mission Objectives To be achieved after Full Operational Capability: 8,000 atmospheric sounding profiles per day 45-min data latency [TBR] Constellation GNSS RO Payload Scientific Payload 6 SC to low-inclinationangle orbit (mission altitude ~520 km) TriG Velocity, Ion Density and Irregularities Instrument RF Beacon Instrument (5+1) or (6+1) SC to highinclination-angle orbit (mission altitude ~800 km) 7 satellites to be allocated for mission design purpose TriG To be determined Launch Vehicle Minotaur IV or Falcon 9 Minotaur IV or Falcon 9 Launch Schedule (as a goal) Communication Architecture 2015 Q3-Q4 2017 Q3-Q4 Via ground station
System Architecture GALILEO or GLONASS-FDMA GPS High-inc Low-inc Spare S/C FORMOSAT-7/ COSMIC-2 TT&C stations (overseas) TT&C stations (Taiwan) US DPC Satellite Operations and Control Center Minotaur IV or Falcon 9 Users Users Fiducial Network Taiwan DPC Researchers Researchers
Mission Constellation 1st Launch 2nd Launch Inclination Angle 24 deg 72 deg Parking Orbit 720 km 550 km Mission Orbit 520 km 800 km Orbital Plane Separation at Equator 60 deg 30 deg
Constellation Deployment Unit:Km 850 800 750 700 650 600 550 500 450 0 12 24 36 48 60 72 84 96 108 120 132 144 156 168 180 192 204 216 1st Launch 2nd Launch Unit:Week Launch Parking Orbit Early Orbit Checkout Mission Payload Starts to Collect Data Adjust the Argument of Latitude Mission Constellation Constellation Deployment Maneuver Orbit Maintenance
Occultations FORMOSAT-3 Occultations 3 Hrs Coverage FORMOSAT-3 FORMOSAT-7 Occultations 3 Hrs Coverage FORMOSAT-7
Spacecraft Bus Requirements
Spacecraft Bus, Satellite, and Multi- Satellites-Suite Science Payloads Mission Payload Spacecraft Bus Satellite
Spacecraft Bus Key Requirements Key Parameter Spacecraft Bus Reliability Power Margin 10% Operations Attitude Attitude Control Accuracy Attitude Determination Knowledge Ground Communication Downlink Telemetry Data Rate Uplink Command Data Rate Spacecraft Bus Data Storage Payload Data Storage Requirements 0.66 for 5 years after launch Local Vertical Local Horizontal better than 1 deg [TBR], 3 σ, all axes better than 0.05 deg [TBR], 3 σ, all axes S band uplink/downlink 2 Mbps 32 Kbps 256 Mbits [TBR] 2 Gbits [TBR]
Conceptual Configuration TriG POD antenna TT&C S-Band antenna VIDI Sensors (may have alternative orientation) TriG OCC antenna (canted or not) Pitch (Y) Roll (X) Ram (Flight direction) RF Beacon antenna Yaw (Z) Nadir TT&C S-Band antenna
Next Step and Acknowledgement Next Steps To firm up segment and interface requirements To implement the corresponding segments Acknowledgements NOAA (National Oceanic and Atmospheric Administration) UCAR (University Corporation for Atmospheric Research) US Air Force JPL (Jet Propulsion Laboratory) Aerospace Corporation NSC (National Science Council) NARL (National Applied Research Laboratory) CWB (Central Weather Bureau) TTFRI (Taiwan Typhoon and Flood Research Institute) Taiwan Science Community
Thanks!