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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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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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.

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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.

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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

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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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