FORMOSAT-7/COSMIC-2 –An Advanced Small Satellite … · 2020. 1. 6. · FORMOSAT-7/COSMIC-2 –An...
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Introduction The role of small satellite constellation in operational meteorology is being increasingly considered, and can potentially provide high impact on certain aspects of Numerical Weather Prediction and weather forecasting. Such systems can provide important additional information addressing specific geographic regions, or address some very specific applications at a suitable price point. This capability has become possible due to innovative payload and measurement techniques, technology miniaturization, and the availability of reliable small satellite technology used in constellations. FORMOSAT-7/COSMIC-2 is a joint program between Taiwan and US to serve as the follow-on “Operational Mission” of FORMOSAT-3/COSMIC, which was a joint US-Taiwan 6-satellite constellation demonstration mission launched in April 2006, to continue the provision of next-generation Global Navigation Satellite System (GNSS) Radio Occultation (RO) data to the global users. The mission aims to collect atmospheric and ionospheric soundings globally through a constellation system of 12 satellites, providing high temporal resolution and high data quality. The design, integration and test (I&T), and verification of the spacecraft heritage from the SSTL-100 bus are important drivers and selected in this joint system in order to obtain measurement data in time for the meteorological forecasting cycle to meet the challenging requirements. This paper provides an overview of the satellite constellation which were carried out to achieve the necessary system design and performance. Keywords: FORMOSAT-7/COSMIC-2, GNSS, Radio Occultation, satellite, constellation, small satellite, Numerical Weather Prediction. FORMOSAT-7/COSMIC-2 – An Advanced Small Satellite Constellation Platform for Numerical Weather Prediction 1 Chen-Joe Fong*, Ming-Shong Chang, Nai-Chen Liu, Jer Ling, Vicky Chu 2 Alex da Silva Curiel, Bernardo Martins, Ed Stevens, Mark Taylor 1 National Space Organization, 8F, 9 Prosperity 1st Road, Science-Based Industrial Park, Hsinchu 30078, Taiwan 2 Surrey Satellite Technology Ltd, Tycho House, Surrey Research Park, Guildford, GU27 YE, United Kingdom *Email: [email protected] Radio Occultation Concept Mission Constellation 6 satellites plus one NSPO-built 720~ 750 km Mission Payload band GNSS RO Receiver Science Payloads Radio Frequency Beacon (RFB) and Ion Velocity Meter Launch Vehicle Falcon Heavy (rideshare) Launch schedule Data Collection Data Latency Communication Architecture S-FTP via VPN Internet Ground Station There shall be sufficient ground stations to meet the data latency requirement Processing FORMOST-7 Mission Baseline Typical 12 hour global sampling pattern FORMOSAT-7 Constellation FORMOSAT-7/COSMIC-2 System Architecture Fiducial Network US DPC TT&C stations (overseas) TT&C stations (Taiwan) Satellite Operations and Control Center Users Researchers FORMOSAT-7/ COSMIC-2 High-inc Low-inc Taiwan DPC GPS GALILEO GLONASS-FDMA Users Researchers Launches Mission Requirements Document (MRD) S/C Reqmts Verification Plan S/C Verifi. Spec S/C Test Req. Doc. S/C Comp. Specs S/C I&T Plan Systems Rqmts Documt. (SRD) EGSE/MGSE Reqmts & Specs S/C Integration & Test (I&T) EMs I&T Comp EMs Test … S/C Test Proc & Test SW EM Test Bench Test Plan SC SDR SRR PDR CDR S/C System Spec. S/C Subsystem Specs S/C Launch Site Processing S/C Mission Constellation Operation PSR ITR FDR Feasibility Design Review MDR Mission Definition Review SRR Systems Requirement Review SDR Systems Design Review PDR Preliminary Design review CDR Critical Design Review ITR Integration &Test Review PSR Pre-Shipment Review MRR Mission Readiness Review Level-One Performance Requirements Document (L1PRD) S/C L&EO and Constellation Deployment FDR Verification Design and Build Units Prototyping MDR SDR MRR SSTL Taiwan End2end Manufacture FS-7B Project Office I&T I&T EVT End2end USA Launch #1 Stand by Fueling Services Support I&T EVT End2end EGSE, MGSE, Simulator EVT Manufacture FS-7A Project Office I&T NPSO delivers US payloads MSS / Sepsys Manufacture FS-7C-F Project Office I&T Taiwan payloads +Z (Nadir) +X (Velocity) +Y • Launch vehicle accommodation • Payload accommodation and Field of View • EMC compatibility • Power and thermal for two orbits FORMOSAT-7/COSMIC-2 Systems Engineering Process (SEP) Stowed Launch configuration on the launcher Spacecraft production flow (first batch of 6) Design challenges Spacecraft stowed configuration Dimensions (stowed) 1000 x 1250 x 1250 mm Launch Mass (wet) 277.8 kg Total Power Peak / OAP 229.8 (orbit average) Battery Capacity > 22.5A-hr Attitude 3-axis Knowledge <0.07deg (3-sigma) Control <1deg (3-sigma) Propulsion Hydrazine monoprop ~141 m/s Communications S-band TM/TC, 32kbps uplink, up to 2Mbps downlink Navigation GPS Design Life 5 years, >66% Availability >95% Launch compatibility EELV (ESPA Grande Adaptor) Payload support >2Gbits data storage 39.4kg mass, 95W OAP Design Features þ dual redundant avionics þ Batch launch compatible þ Constellation compatible Satellite Specification 10th FORMOSAT-3/COSMIC Data Users' Workshop and 6th International Radio Occultation Working Group (IROWG-6) meeting, Estes Park, CO, Sep. 21-27, 2017. FORMOSAT-7 First Launch Second Launch Mission Objectives To be achieved after Full Operational Capability: n Average 8,000 atmospheric sounding profiles per day n 45-min data latency for neutral atmosphere data n 30-min data latency for ionospheric data Constellation 6 Mission Spacecraft Mission altitude 520~550 km Low-inclination: 24 deg. 6 Mission Spacecraft + 1 NSPO- Build SC Mission altitude 720~750 km High-inclination: 72 deg GNSS RO Payload Tri-band GNSS Receiver System (TGRS) Tri-band GNSS Receiver System (TGRS) Scientific Payload US Furnished Ion Velocity Meter (IVM) RF Beacon (RFB) Transmitter Taiwan Furnished Scientific Payload Mission Life 5 Years beyond the second launch Launch Vehicle US furnished Falcon- Heavy (Rideshare) US furnished EELV-like with a 5-m fairing Launch Schedule 2Q Year 2017 [TBD] Communication Architecture Via ground station
Transcript of FORMOSAT-7/COSMIC-2 –An Advanced Small Satellite … · 2020. 1. 6. · FORMOSAT-7/COSMIC-2 –An...
IntroductionThe role of small satellite constellation in operational meteorology is being increasingly considered, andcan potentially provide high impact on certain aspects of Numerical Weather Prediction and weatherforecasting. Such systems can provide important additional information addressing specific geographicregions, or address some very specific applications at a suitable price point. This capability has becomepossible due to innovative payload and measurement techniques, technology miniaturization, and theavailability of reliable small satellite technology used in constellations.
FORMOSAT-7/COSMIC-2 is a joint program between Taiwan and US to serve as the follow-on“Operational Mission” of FORMOSAT-3/COSMIC, which was a joint US-Taiwan 6-satellite constellationdemonstration mission launched in April 2006, to continue the provision of next-generation GlobalNavigation Satellite System (GNSS) Radio Occultation (RO) data to the global users. The mission aims tocollect atmospheric and ionospheric soundings globally through a constellation system of 12 satellites,providing high temporal resolution and high data quality.
The design, integration and test (I&T), and verification of the spacecraft heritage from the SSTL-100 busare important drivers and selected in this joint system in order to obtain measurement data in time for themeteorological forecasting cycle to meet the challenging requirements. This paper provides an overview ofthe satellite constellation which were carried out to achieve the necessary system design and performance.
Keywords: FORMOSAT-7/COSMIC-2, GNSS, Radio Occultation, satellite, constellation, small satellite,Numerical Weather Prediction.
FORMOSAT-7/COSMIC-2– AnAdvancedSmallSatelliteConstellationPlatformforNumericalWeatherPrediction
1Chen-Joe Fong*, Ming-Shong Chang, Nai-Chen Liu, Jer Ling, Vicky Chu2Alex da Silva Curiel, Bernardo Martins, Ed Stevens, Mark Taylor
1National Space Organization, 8F, 9 Prosperity 1st Road, Science-Based Industrial Park, Hsinchu 30078, Taiwan2Surrey Satellite Technology Ltd, Tycho House, Surrey Research Park, Guildford, GU27 YE, United Kingdom
*Email: [email protected]
Radio Occultation Concept
First Launch Second Launch
Mission Constellation 6 satellites 6 satellites plus one NSPO-built satellite
MissionOrbit
Inclination: 24 degParking altitude: 720 km
Mission altitude: 520~550 km
Inclination: 72 degParking altitude: 520 km
Mission altitude:720~ 750 km
Mission Payload Tri-band GNSS RO Receiver System (TGRS)
Tri-band GNSS RO Receiver System (TGRS)
Science PayloadsRadio Frequency Beacon
(RFB) and Ion Velocity Meter (IVM)
Taiwan-furnished payload(s)
Launch Vehicle Falcon Heavy (rideshare)ESPA Grande Ring
Falcon-9, Falcon Heavy, or EELV (rideshare)
Launch schedule 2Q 2018 2020 (TBD)
Data Collection Average 10,000-12,000 useful tropospheric data collections per day
Data Latency 30 minutes (ionospheric data), 45 minutes (neutral atmospheric data)
Communication Architecture S-FTP via VPN Internet
Ground Station Requirement
There shall be sufficient ground stations to meet the data latency requirement
Data Processing Centers US-DPC and Taiwan-DPC
FORMOST-7 Mission Baseline
Typical 12 hour global sampling patternFORMOSAT-7 Constellation
FORMOSAT-7/COSMIC-2 System Architecture
FiducialNetwork
US DPC
TT&C stations (overseas)
TT&C stations (Taiwan)
Satellite Operations and Control Center
Users Researchers
FORMOSAT-7/COSMIC-2
High-inc
Low-inc
Taiwan DPC
GPSGALILEO GLONASS-FDMA
Users ResearchersLaunches
Mission Requirements
Document (MRD)
S/C ReqmtsVerification PlanS/C Verifi. SpecS/C Test Req. Doc.
S/C Comp.Specs
S/C I&TPlan
Systems RqmtsDocumt. (SRD)
EGSE/MGSEReqmts& Specs
S/C Integration &
Test (I&T)
EMs I&T
Comp EMsTest
…
S/C TestProc & Test
SW
EM Test BenchTest Plan
SC SDR
SRR
PDR
CDR
S/C System Spec.
S/C SubsystemSpecs
S/C Launch SiteProcessing
S/C Mission Constellation
Operation
PSR
ITR
FDR Feasibility Design ReviewMDR Mission Definition ReviewSRR Systems Requirement ReviewSDR Systems Design ReviewPDR Preliminary Design reviewCDR Critical Design ReviewITR Integration &Test ReviewPSR Pre-Shipment ReviewMRR Mission Readiness Review
Level-One PerformanceRequirements
Document (L1PRD)
S/C L&EO andConstellationDeployment
FDR Verification
Design and Build Units
Prototyping
MDR
SDR
MRR
SSTL
Taiwan
End2end
ManufactureFS-7B
Project Office
I&T
I&T
EVT
End2end
USALaunch
#1
Stand by
Fueling Services
Supp
ort
I&T
EVT
End2end
EGSE, MGSE, Simulator
EVT
ManufactureFS-7A
Project Office
I&T
NPSO delivers US payloads
MSS / Sepsys
ManufactureFS-7C-F
Project Office
I&T
Taiwanpayloads
+Z (Nadir)
+X (Velocity)
+Y
• Launch vehicle accommodation
• Payload accommodation and Field of View
• EMC compatibility
• Power and thermal for two orbits
FORMOSAT-7/COSMIC-2 Systems Engineering Process (SEP)
Stowed Launch configuration on the launcher
Spacecraft production flow (first batch of 6)
Design challenges
Spacecraft stowed configuration
Dimensions (stowed) 1000 x 1250 x 1250 mmLaunch Mass (wet) 277.8 kgTotal Power Peak / OAP 229.8 (orbit average)Battery Capacity > 22.5A-hr
Attitude3-axis Knowledge <0.07deg (3-sigma)Control <1deg (3-sigma)
Propulsion Hydrazine monoprop ~141 m/s
CommunicationsS-band TM/TC, 32kbps uplink, up to 2Mbps downlink
Navigation GPSDesign Life 5 years, >66%Availability >95%Launch compatibility EELV (ESPA Grande Adaptor)
Payload support>2Gbits data storage39.4kg mass, 95W OAP
Design Featuresþ dual redundant avionicsþ Batch launch compatibleþ Constellation compatible
Satellite Specification
10th FORMOSAT-3/COSMIC Data Users' Workshop and 6th International Radio Occultation Working Group (IROWG-6) meeting, Estes Park, CO, Sep. 21-27, 2017.
FORMOSAT-7 First Launch Second Launch
Mission Objectives
To be achieved after Full Operational Capability:n Average 8,000 atmospheric sounding profiles per dayn 45-min data latency for neutral atmosphere datan 30-min data latency for ionospheric data
Constellation
6 Mission SpacecraftMission altitude 520~550 kmLow-inclination: 24 deg.
6 Mission Spacecraft + 1 NSPO-Build SC Mission altitude 720~750 kmHigh-inclination: 72 deg
GNSS RO Payload
Tri-band GNSS Receiver System (TGRS)
Tri-band GNSS Receiver System (TGRS)
Scientific Payload
US FurnishedIon Velocity Meter (IVM)RF Beacon (RFB) Transmitter
Taiwan Furnished Scientific Payload
Mission Life 5 Years beyond the second launch
Launch Vehicle US furnished Falcon-Heavy (Rideshare)
US furnished EELV-like with a 5-m fairing
Launch Schedule 2Q Year 2017 [TBD]
Communication Architecture Via ground station
CONCLUSIONThe FORMOSAT-7 missions demonstrate that small satellites can play a significant role in operationalmeteorology. The system also demonstrates the concept of a highly integrated distributed system, asthe ground network and space system must be carefully designed in order to meet the tight operationalconstraints of the mission. The system also completely relies on the availability of another group ofconstellations of the Global Navigation Satellite Systems, in order to support the sensor. FORMOSAT-7will only meet its objectives as a complete system, covering both planned orbit planes. Without thesecond batch in orbit in time there will be no high latitude coverage.
The FORMOSAT-7 spacecraft bus design is well suited for other constellations or single satellitemissions, provides very high payload mass fraction, and exceptional power fractions for the size of thespacecraft.
Satellite Electrical Configuration
SC Deployed Configuration
POD OCCRF Beacon
IVM
Payload FOVs Challenge
SSTL-100
Orbit PlaneChanges
Accommodate 6-7 s/c on Minataur-IV
Add high-delta-vee propulsion
system
Compatibility With existing
Ground segment
Select suitable
OBC
Update receiver
Pointing requirements
Update Attitude Control
Software
Add StarCam(s)
Non sun-sync orbits
ReconfigureSolar Panel arrangement
Remove DMCpayload
OBC capability
Large/heavy Payloads
More payloadpower
Flight softwareupdates
Update thermal design
New structure+sep system
Spacecraft Development Plan
Satellite Verification Process
Verification Test Matrix
FM3 ACOUSTIC TEST
PFM ELECTROMAGNETIC COMPATIBILITY (EMC) TEST
FM3 THERMAL VACUUM (TVAC) TEST
FM3 FIT-CHECK
SC Exploded View
NSPO I&T FacilitiesHsinchu Science Park
• Base area: 13,102 square meters• Construction area: 6,162 square meters• Building dimensions: 115 meters× 53 meters× 17 meters （ height ）• Floor area: 12,676 square meters• Floor level: 1 basement level and 2 above ground levels• Building completion and open for use: in July 1997
10th FORMOSAT-3/COSMIC Data Users' Workshop and 6th International Radio Occultation Working Group (IROWG-6) meeting, Estes Park, CO, Sep. 21-27, 2017.
