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Toshinori Kuwahara Tohoku University,

3rd Nano-Satellite Symposium

December 13, 2011

Contents

Project background Instruments selection process/ selected instruments System design conditions RISESAT system architecture Configuration of science handling unit Conclusion

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Project Background

Hodoyoshi Program (Professor Nakasuka, The University of Tokyo) Development of five 50kg class micro-satellites Launch is planned in the Japanese fiscal year of 2013 One of the five is an international scientific micro-satellite (RISESAT) (Tohoku University is responsible for the project management)

RISESAT: Rapid International Scientific Experiment Satellite Mission Objectives Demonstrate international scientific missions by inviting instruments from abroad Investigation on advanced bus system technologies for future scientific micro-

satellites Development of a reliable, robust and cost effective micro-satellite bus system Expected effects Realization of mechanism of rapid demonstration of scientific missions in the future Improvement of microsatellite technologies which enables future challenging

scientific missions Commercial spin-off of providing cost-effective microsatellite bus systems

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#1：SPRITE-SAT (RISING-1) Launch: Jan. 2009 (H-IIA) Demonstration of

Image acquisitions by mission camera Coarse attitude control Deployment of the boom TAMU: Tohoku-Ångström MEMS Unit

#2：RISING-2 Under development (- Sep 2011)

FM system integration and verification Software update

Mission Multi-spectrum observation with a Liquid Crystal

Tunable Filter (650-1000nm) High resolution stereo images of cumulonimbus Terrestrial luminous events in upper atmosphere TAMU-2

To be launched around 2013

Small satellite development at Tohoku University

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Tohoku University has experience of 50 kg small satellite development

(Design, Development, Test, Launch, Operation)

Scientific Payload Invitation

Call for Letter of Intent (Sep. 27 2010) 16 LOI submitted (Vietnam,

Hungary, Czech, Taiwan, Canada, Thailand, USA, Sweden, Ukraine, Turkey, Germany)

6 are selected MOUs

FTRI (Vietnam) April (2 visits) NCU (Taiwan) May (3) KFKI (Hungary) June (1) IEAP (Czech) July (2) NCKU (Taiwan) October (2) ASTC (Sweden) soon… (2)

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Scientific Instruments

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# Representative Institute Country Missoin/Instruments MOU

1 Dr. Yi Chou Graduate Institute of Astronomy, National Central University

Taiwan High Precison Telescope (HPT)

#1.0

2 Dr. Trung The Tran FPT Technology Research Institute, FPT University

Vietnam Camera sensor electronics for HPT

#1.0

3 Dr. Janos Gado / Dr. Attila Hirn

Hungarian Academy of Sciences KFKI Atomic Energy Research Institute

Hungary three dimensional silicon detector telescope

#1.0

4 Dr. Nguyen Angstrom Space Technology Centre Sweden 3 D Magnetometer Arrangement

5 Dr. Carlos Granja Insitute of Experimental and Applied Physics (IEAP) Czech Technical Univereity (CTU)

Czech Compact space radiation micro-tracker （TIMEPIX）

#1.0

6 Prof. Alfred Bing- Chih Chen

National Cheng Kung University Space & Plasma Science Center and Department of Physics

Taiwan Lightning/meteor detector #1.0

7 Prof. Rene Laufer et.al.

Beylor University/ Stuttgart University/ TU Dresden et.al.

Germany/USA/France/GB/Australia

Store&Forward global carbon monitoring

To be arranged

8 Dr. Kuwahara Tohoku University Japan Ocean Observation Camera

Scientific Instruments

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High Precision Telescope - HPT

(Taiwan(NCU)/ Vietnam)

TriTel – 3D Dosimeter (Hungary)

TIMEPIX – Particle counter (Czech)

SDTM – MEMS Magnetometer (Sweden)

Meteor counter - DOTCam

(Taiwan(NCKU))

Ocean Observation Camera - OOC (Tohoku University)

Camera Instruments

Sensor Instruments

Earth and Planetary Observation Telescope (Taiwan-Vietnam)

Inherit technologies of RISING-2 Joint project between:

Tohoku University Hokkaido University National Central University (Taiwan) FPT University (Vietnam)

Performance GSD: 5m Focal Length: ~ 1000mm Diameter: ~ 100mm Filter:

SDSS and others (under arrangement) In total 6 channels

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TriTel: 3D silicon detector telescope (Hungary), KFKI

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x

Y

Z

θ

φ

Measuring Detector

Coincidence Detector

Almost uniform sensitivity in 4 π Deposited energy spectra (silicon) + time spectra An assessment of the anisotropy of the radiation field is possible LET spectrum: 0.2 keV/ μ m – 120 keV/μm in water

1D detector x

Y

Z Z-telescope

X-telescope Y-telescope

3D detector

TIMEPIX (Czech), IEAP

High resolution and high sensitivity voxel detector which can directly determine the entire charged particle spectrum from electrons, protons and up to relativistic heavy ions

Based on the stack of position-sensitive semiconductor detector Timepix, which works as a radiation micro-telescope

Each pixel is equipped with its own integrated spectrometric signal chain which allows in any pixel to count the number of particles, measure the energy deposited or register the time of interaction

Characteristics Power: Single 5V DC source with less than 15W Weight: 1 kg Size: 20 cm x 10 cm x 15 cm.

10 Timepix

Voxel

Dual-band Optical Transient Camera (DOTCam), NCKU

Detect meteor and lightning Watec T065 CCD

659 x 494 pixels 7.4um x 7.4um

Lens: f=12mm, F/1.4 FOV: 22º x 16.5º @ 800km 1 W, 5V (tentative) 800g Data compression ratio > 2.5 Size: 108mm x 70mm x 100mm Modes: continuous acquisition, time-tagged snapshot, single

color trigger, two colors trigger

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Ocean Observation Camera, Tohoku University SPA (Space Plug & Play)

compatible Watec T065 CCD

659 x 494 pixels 7.4um x 7.4um

Lens: f=12mm, F/1.4 < 3W, 5V ~ 1000g Filter

3 channels under arrangement

High-speed acquisition 9 pictures /s (continuous) Synchronous acquisition

COTS products: BGA 12

RISESAT System Specification

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Specification

Launch configuration

After panel deployment

Design Conditions Design Conditions Mass: < 55kg (Payloads > 20 %) Size: < 50cm x 50cm x 50cm Design life time: > 2 years Sun Synchronous Orbit Orbit Altitude: 500 - 900 km (Default:800km)

Inclination: ~98° LTDN/LTAN： 9:00 ～15:00 (Default: LTDN 11:00)

Piggy-back launch compatible Several launchers: H-IIA, DNEPR, etc. Mass：Need to reduce mass down to < 50 kg for H-IIA Exchange interface adapter depending on the launcher

Design objectives Attitude control error (requirement): < 0.1º Attitude control error (objective): < 0.01º (36'') Attitude control stability: <6 º/h Power generation capability: > max. 100W Max. possible power consumption: > 50W (day side/night side) Mission data downlink: > 2Mbps

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12:00 11:00: Default

9:00 15:00

15º 30º

LTDN

N

Sun

[URX] UHF

receiver

[STX] S-band

transmitter

[CTR] Command and

telemetry router

[PCU] Power control

unit

Payload 2 FPTI

[ACU] Attitude Control

Unit [MTQ] Magnetic Torquers (3-axes)

[GAS] Geomagnetic

Sensor (3-axes)

[SAS] Coarse sun

sensors

[RW] Reaction wheels (4)

[STT] Star Trackers (2)

[FOG] Gyroscope (3-axes)

[SES] Sun earth sensors (4)

Payload 3 NCKU

Payload 4 KFKI

[GPSR] GPS receiver

[BAT] Battery unit

[SCP] Solar cells

[MMC] Micro monitor

camera

[DOM] De-orbit

Mechanism

[SPDM] Solar Panel Depl. Mech.

Scientific Data Line

Power Line

Main Bus Com. Line

Other General Lines

[UHYB] UHF

antenna hybrid

[XTX] X-band

transmitter

Telemetry, Tracking & Command Command & Data Handling Orbit determination

Fine Attitude Control System

Power Supply System

High-speed Downlink

[SCU] Satellite central unit

New Development

Re-design [CPU-N]

Processor unit (nominal)

[CPU-R] Processor unit

(redundant)

Main computing unit

Antifuse FPGA

[DPD] Data

Decoder

[TTR] Telecommand,

telemetry, and recovery

Payload 5 ASTC

Coder

Payload 6 IEAP

[SHU] Science handling unit

Payload 1 NCU Payload

Coarse Attitude Control System

4R1_2011/10/17

System Architecture

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[URX] UHF

receiver

[STX] S-band

transmitter

[CTR] Command and

telemetry router

[PCU] Power control

unit

[ACU] Attitude Control

Unit [MTQ] Magnetic Torquers (3-axes)

[GAS] Geomagnetic

Sensor (3-axes)

[SAS] Coarse sun

sensors

[RW] Reaction wheels (4)

[STT] Star Trackers (2)

[FOG] Gyroscope (3-axes)

[SES] Sun earth Sensors (4)

[BAT] Battery unit

[SCP] Solar cells

[DOM] De-orbit

Mechanism

[SPDM] Solar Panel Depl. Mech.

[UHYB] UHF

antenna hybrid

[XTX] X-band

transmitter

Telemetry, Tracking & Command Command & Data Handling Orbit determination

Fine Attitude Control System

Power Supply System

Payload

High-speed Downlink

[SCU] Satellite central unit [CPU-N]

Processor unit (nominal)

[CPU-R] Processor unit

(redundant)

[TTR] Telecommand,

telemetry, and recovery

Nominal ON

To be defined

General supply

Bus supply

Main computing unit

Antifuse FPGA

[MMCU] Micro monitor

camera unit Coder [SHU]

Science handling unit

[GPSR] GPS receiver

Payload 2 FPTI

Payload 3 NCKU

Payload 4 KFKI

Payload 5 ASTC

Payload 6 IEAP

Payload 1 NCU

Coarse Attitude Control System

4R1_2011/10/17

Power Distribution Architecture

[DPD] Data

Decoder

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Structural Configuration

Z

X Y

Z

X Y

Z

X

Y

UHYB+URX+STX

Z Y

MMC

STT STT

STT

ACU+SCU

RW

ACU+SCU

ACU+SCU LLT

DOTCAM

GAS

GPS_R

GPS_R

GAS

SES X-ANT

SES SES

GPS

GPS

OOC

DOTCAM

ACU+SCU

S-ANT

HPT

MMC

U-ANT

X-ANT

S-ANT

X

DM MMC

Bus Components Section

Payload Section 17

DOTCam

HPT

TriTel

HPT_HU

SDTM TIMEPIX

Laser Link Terminal

MMC_Elc

Z

X

Z

X

Y

Z

X

PCU BAT

FOG

SHU

SHU

FOG PCU

BAT

Payload Configuration

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Interface Window between SHU and payload instruments

MPDU

PCU

RTU 500 (26 GPIO)

SCU

XTX

DPCU-U1

uRTU

GPIO

Mem.

Cam 1 Cam 2

Mass Memory (16 GB)

2.45 Mbps

SHU USB1.1 Network 12Mbps

15W each (not together)

Instruments Control Unit

Particle Counter

SHU Electrical Architecture

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9.9V+100mV,-0mV ~15.0V+/-100mV

[MMC] Micro

monitor camera

5V 12V

DC/DC 18V

DC/DC 5V

Coder

DPCU-U2

uRTU

GPIO

Mem.

SDTM

uRTU

GPIO

Mem.

TriTel Dosimeter

uRTU

GPIO

Mem.

DOTCam

Meteor Observation

Camera

Cam 3

uRTU

GPIO

Mem.

OOC

Ocean Observation

Camera

Cam 1 Cam 6

uRTU

GPIO

Mem.

Earth/

Planetary Observation

Camera

Cam 1

VSI

uRTU

GPIO

Mem.

Laser Link

Terminal

DC/DC TBD

5V (Power only)

SPA-U (Signal only)

SPA-U

5V

5V

TTL (GPIO)

RS422

RS422 (GPIO)

Cam 3

CHU1

VSI Specification

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System On-Board

Computer with Plug-and-Play

System Manager at

Locatation A

Plug-and-Play Network

Viritualizer at Location A

Plug-and-Play Network

Viritualizer at Location B

Intelligent Plug-and-Play

Power Distribution

Unit

Plug-and-Play interface with

Driver / Datasheet

Virtual System Integration via Internet

Effective system integration for international satellite missions

Application of VSI

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©Wikipedia

Schedule

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Conclusion

More than 6 international scientific instruments are on-board the micro-satellite RISESAT.

The satellite system design is almost done. The interface between the satellite and scientific

instruments are now under implementation.

MTM vibration test starts Dec 2011 System EM assembly by March 2012 System FM assembly by March 2013 Launch Nov. 2013 (planned)

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Thank you very much for your kind attention.

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