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1This document contains proprietary and controlled information of National Space Organization (NSPO) of Taiwan and shall not be duplicated in whole or in part for any purpose without permission from NSPO.
Chen-Joe Fong, Nick L. Yen, Eddy Yang, Chung-Huei Chu, Jer Ling, Tiger Liu, and Guey-Shin Chang
National Space Organization (NSPO)
2012.11.1
Sixth FORMOSAT-3/COSMIC Data Users' Workshop, 30 - 1 November 2012, Boulder, CO.
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3,165,792 Profiles
FORMOSAT-3/COSMIC Radio Occultation Profiles(10-30-2012)(10-30-2012)Atmospheric
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500
1000
1500
2000
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3000
4/15/06 10/15/06 4/15/07 10/15/07 4/15/08 10/15/08 4/15/09 10/15/09 4/15/10 10/15/10 4/15/11 10/15/11 4/15/12 10/15/12
Data Point
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200
400
600
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1000
1200
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1600
1800
FS3/C RO production RO production increased recently after Ground
operation to adjust charging control regarding to different beta angle and different satellite.
Recent 60 days average is about 1500 profiles produced by 5 satellites. (the largest RO production in two year average is 1700 produced by 6 satellite)
Average in two month
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Formosat-3 StatusFormosat-3 StatusSC Bus IGOR
FM1Bad Attitude due to sun sensor noise
IGOR 100% duty, only one side POD is functional
FM2 Half solar array power IGOR 100% duty when 10 < |beta| < 57
FM3 Phoenix mide since 2010/6
FM4 Battery aging
GOX turn off in whole eclipse period when eclipse time larger than 25 minutes, only one side POD is operational
FM5 Normal GOX 100% duty, SNR drop in higher beta, only one side POD is operationl
FM6 Normal GOX 100% duty, 1 OCC (RF4) totally gone, only one side POD is operational
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FORMOSAT-7/COSMIC-2 Constellation
1st Launch 6 SC to a parking orbit with
inclination angle of 24~28.5 deg.
Through constellation deployment, 6 SC will be separated to 6 orbital planes with 60-deg separation.
2nd Launch 6 SC to a parking orbit with
inclination angel of ~72 deg. Through constellation
deployment, 6 SC will be separated 6 orbital planes with 30-deg separation.
NSPO-built satellite will be sent to the space by the 2nd launch (green dash line).
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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
6 SC to low-inclination-angle orbit (mission altitude 520~550 km)
(5+1) or (6+1) SC to high-inclination-angle orbit (mission altitude 720~750 km)
7 satellites to be allocated for mission design purpose
GNSS RO Payload
TriG GNSS Radio occultation
System TriG GNSS Radio occultation System
Scientific Payload
US furnishedVIDI and RF Beacon Instrument
Taiwan furnished
Launch Vehicle Equivalent to Atlas-5 or Delta-4 (rideshare) Minotaur IV series or Falcon 9
Launch Schedule (as a goal) No earlier than 2015 Q4 2018 Q2-Q3
Communication Architecture Via ground station
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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
GPS GALILEO or GLONASS-FDMA
Spare S/CSpare S/C
Users Researchers
Launch Vehicles
Mission Architecture
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F7/C2Executive Steering
Committee
TECRO AITAIT-TECROAgreement
FORMOSAT-7 / COSMIC-2Joint Program
Management Office
NOAANSPO
NARLFORMOSAT-7 /
COSMIC-2 Mission
FORMOSAT-7 Program Management
Office(NSPO)
COSMIC-2 Program Management
Office(NOAA)
NSC
FORMOSAT-7 / COSMIC-2 Joint Management
Control Plan
DOC
NSC: National Science Council NARL: National Applied Research LabNSPO: National Space OrganizationTECRO: Taipei Economic and Cultural Representative Office AIT: American Institute in TaiwanDOC: Department Of CommerceNOAA: National Oceanic and Atmospheric Administration
Supervision and Guidance
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Joint Program
WBS 1.0Program
Management
WBS 2.0System
Engineering
WBS 3.0Mission
Assurance
WBS 4.0Satellite
Development
WBS 5.0Launch
WBS 6.0Ground & Mission
Operations
WBS 7.0Data
Processing
System Analysis
System & Interface
System Verification
System Operations
SL for Launch #1
SL for Launch #2
NSPO-Built SL
NSPO Mission
Assurance
NOAA Mission
Assurance
Launch #1
Ground System
Frequency Coordination
Mission Operations
US DPC
Taiwan DPC
DPC IF
Advisory & Supervision
Joint Program
Management
NSPO Program
Management
Launch #2
WBS 8.0Data
Utilization
BusMission
PLScience
PLMSD
BusMission
PL
US RO Data Utilization
Taiwan RO Data
Utilization
US Science Data
Application
Taiwan Science Data Application
NOAA Program
ManagementSL AIT
BusMission
PLScience
PLMSD
SL AIT
Responsible by Both Side
Responsible by NOAA
Responsible by NSPO
SL: SatellitePL: PayloadMSD: Multi-Satellite DispenserAIT: Assembly, Integration , and TestDPC: Data Processing CenterIF: InterfaceRO: Radio Occultation
FORMOSAT-7/COSMIC-2 Joint Program
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Radio Occultation ApplicationProvide data for regional
forecasting and global forecasting
Enhance the accuracy for severe weather forecast
Monitor the space weather Provide data for climate
trending
Establish Taiwan’s Capabilities in Space Industry Procure mission satellites Develop NSPO-Built satelliteProvide the opportunity to
domestic researchers to develop science payload
Develop indigenous components
International Cooperation Execute agreement between Taiwan and the US to provide radio
occultation data Promote the cooperation with Europe and Asian on the related
studies.
Goals of FORMOSAT-7 Program
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Data Distribution after the 1st Launch
5770 raw radio occultation profiles by 6 SC, the data distribution is within a band of ± 50 deg latitude.
13
Data Distribution after the 1st and the 2nd Launch
11958 raw radio occultation profiles by 6 SC from the 1st launch (yellow dots)
and 6 SC from the 2nd launch (red dots).
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Area: 0~50N, 100~150E
FORMOSAT-3
(GPS signal only)
120 profiles
FORMOSAT-7
(the first 6 satellites)
(GPS & GLONASS signals)
408 profiles
FORMOSAT-7
(12 satellites)
(GPS & GLONASS signals)
703 profiles
Data Distribution Simulation Around Taiwan Region
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Data Processing• US will develop data processing center and the
software will be installed in US Data Processing Center and Taiwan Data Processing Center.
• Taiwan will develop verification software. It is implemented by NSPO, Central Weather Bureau, and GPSARC center.
Data Application• The mission data will be made available on open
basis. • In Taiwan, the data application study is carried out
by Taiwan Typhoon and Flood Research Institute, Central Weather Bureau, and GPSARC center.
16
Interface Development• Bus to payload• Launch vehicle to MSS• Mission Satellites to NSPO-
Built Satellite
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Dimensions (stowed) 963 (L) mm x 621 (W) mm x 2257 (H) mm
Launch Mass (wet) 215kg
Total Power Peak / OAP 325W / 325-205W
Battery Capacity 22.5A-hr
Attitude3-axis Linear ControlKnowledge <0.07deg (3-sigma)Control <1deg (3-sigma)
PropulsionHydrazine monoprop194 m/s
CommunicationsS-band TM/TC, 32kbps uplink, up to 2Mbps downlink
Navigation GPS
Design Life 5 years, >66%
Availability >95%
Launch compatibility Minotaur-IV, Falcon-9, EELV New Entrant
Payload support>2Gbits data storage39.4kg mass, 95W OAP
Design Features dual redundant avionics Batch launch compatible Constellation compatible
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Courtesy from USAF AFSPC SMC/WMA
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Courtesy from USAF AFSPC SMC/WMA
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ITT Antenna and RF Beacon Electronics Design
Courtesy from USAF AFSPC SMC/WMA
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SRI Antenna and RF Beacon Electronics Design
Courtesy from USAF AFSPC SMC/WMA
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Courtesy from Surrey Satellite Technology LTD
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– 2A
Sp
acec
raft
Occultation Antenna
POD Antenna
POD Antenna
Occultation Antenna
LNAs(inside structure)
TriG Receiver
RF Beacon (deployed volume)
VIDI (IVM)
VIDI (SPLP)
RF Beacon sensor electronics (inside structure)
LRRs (on nadir panel beside RF beacon volume)
+Z(Nadir)
Courtesy from Surrey Satellite Technology LTDCourtesy from Surrey Satellite Technology LTD
25
Nadir Nadir
Bottom viewCourtesy from Surrey Satellite Technology LTD
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Smallest of the Possible Launch Volumes for Minotaur-IV
Dynamic envelope
Courtesy from Surrey Satellite Technology LTD
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NSPO Spacecraft
NSPO Spacecraft
Courtesy from Surrey Satellite Technology LTD
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OBC
PCDU
FOG
GPS Receiver
Courtesy from Surrey Satellite Technology LTD
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–PCDU
NSPO Built Satellite■ System Electrical Configuration■ Satellite System Specification
On-board Computer■ Prototype Design■ Detail Spec. Definition
PCDU■ Prototype Design■ Detail Spec. Definition
Bus GPS Receiver■ Radiation and TV Test■ FM Circuit Design
Optical Fiber Gyro■ 1-Axis Complete■ 3-Axes Prototyping
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Target Second Launch Target First Launch
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Program Progress• The joint program has completed
Mission Definition Review, System Requirement Review, and System Design Review.
• By the end of 2012, all payload Critical Design Reviews are expected to be completed, Bus Spacecraft System Design Review will have been conducted, and the launch vehicle for the first launch is to be announced.
2009.8 MDR
2010.4 SRR
2010.6 SDR2012.9 SC Bus Kick-Off
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Issues and Concerns The key issue, such as the 2nd launch, is scheduled
to be resolved by the Executive Steering Committee meetings in 2013.
The programmatic and technical discussion will happen in Joint Program Management Office meeting, Technical Interface Meeting, and Interface Control Working Group.
2011.10 JPMO#102012.2 ESC#3
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討論議題
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