Introduction of Graduate School of Science, the University of Tokyo and Associated

Institute (ISAS/JAXA)and

Suggestions on SpaceMaster Thesis ThemesMasafumi HIRAHARA

Space and Planetary Science Group,Department of Earth and Planetary Science,

Graduate School of Science, The University of Tokyo（email: hirahara@eps.s.u-tokyo.ac.jp） (skype: masa.hirahara)

http://www.s.u-tokyo.ac.jp/en/ http://www.eps.s.u-tokyo.ac.jp/index_en.html

Departments in Graduate School of SciencePhysicsAstronomyEarth and Planetary Science (EPS)ChemistryBiophysics and BiochemistryBiological Sciences

Research Groups in Our DepartmentAtmospheric and Oceanic Science GroupSpace and Planetary Science GroupEarth and Planetary System Science GroupSolid Earth Science GroupGeosphere and Biosphere Science Group

Introduction of myself• Solar-terrestrial physics (STP), Space (plasma) physics• Auroral and geospace/planetary explorations through

satellites and spacecraft operations from ground-based sites

• Developments of plasma/particle instruments and associated calibration facility for in-situ observation in space

• Experimental/data analysis works for space plasma/particle observationsToday I am a representative of three research groups; two in Univ. Tokyo and one in ISAS/JAXA.

1. Space instrumentation/data analysis in Hongo of Univ. Tokyo2. Planetary research in Kashiwa of Univ. Tokyo3. Satellite component development in Sagamihara of ISAS/JAXA

Solar wind plasma stream and interplanetary magnetic field(Expansion of solar corona)

Terrestrial upper atmosphereand intrinsic magnetic field

Mercury’s magnetospheric formation andacceleration of space plasma particles due tointeraction between solar wind and Mercury’sIntrinsic magnetic field

Mercury magnetosphericexploration mission

Atmospheric escape/evolution and climatechange due to direct interaction between solar wind and Martian ionosphere

Solar-TerrestrialEnvironment

Mercury Mars

Sun

Earth

Geospace-magnetosphere

Solar wind

Radiation belt(Van Allen belt)

Gespace-ionosphereRing current

Graduate School of Science (GSS),the University of Tokyo (UT)

Main Island of Japan

Central Area of TokyoCentral Tokyo

Akihabara

Univ. TokyoIn Hongo Area

Campuses of Univ. TokyoHongo, Komaba, Kashiwa,Shirokane, Nakano

Graduate School of Science (GSS),the University of Tokyo (UT)

Main Island of Japan

Central Area of TokyoCentral Tokyo

Akihabara

Univ. TokyoIn Hongo Area

Hongo Campus of Univ. Tokyo

GSS of UT forSpaceMaster

Campuses of Univ. TokyoHongo, Komaba, Kashiwa,Shirokane, Nakano

In Hongo campus of Univ. Tokyo

Master Themes in Hongo of Univ. Tokyo• Construction and automation of ion/electron beam facility for

calibrating space plasma/particle instruments for BepiColomboMercury magnetosphere and future terrestrial/planetary explorations– 1 – 200 keV ion/electron beam line – Beam line profiling and calibration system control– Final calibration for BepiColombo high-energy ion sensor– A few eV – a few tens of keV ion beam line

• Design of suprathermal ion energy/mass spectrometers for future terrestrial/planetary explorations– Polar-ionosphere and Geospace explorations– Martian upper atmosphere and ionosphere exploration

• Data display/analysis system for auroral images and plasma particle data– Auroral imaging camera data from Reimei and ALIS– Google Earth or other visualization platform

SunSolar Wind

Auroral Camera

Geospace-Ionosphere

Aurora

Magnetometer

ORBITALS

Radiation BeltsRing Current

RBSP

ERG

RadarLidarHeater

International Geospace Observation Network

RESONANCE

KuaFu

LANLGOES

POES

Geospace-Magnetosphere

THEMIS

GeotailCluster II

AkebonoFAST

Reimei

FORMOSAT-5

CASSIOPE

Earth

Radiation Belts(Van Allen Belts)

Ring Current

Magnetosphere

Sun

Ionosphere

Solar Wind

PlasmaSheet

Geospace

plasmasphere

ring current

plasma sheet

inner belt outer belt

1 eV

100 keV

1 MeV

Space Plasma/Particle Energy Distributionin Geospace

LEP-i

MEP-i

HEP-i

1 keVLEP-e

MEP-e

HEP-e

XEP

10 MeV

ion(H+, He+, O+)

electron

Plasma/particle instrument package has to cover a wide energy range over more than 7 orders.

L=5 ReL=2 Re

TSP-i TSP-e

Altitude from Earth

Ene

rgy

Calibration Facility for Space Plasma/Particle Instruments～200-keV ion/electron beam line

IsolationTransformer

(200kV)High-voltage power supply （+50kV）

High-voltage power supply （+150kV）

Vacuum chamber

Vacuum pumps

Turntableand X-stage

Isolation tube with linear accelerator

Ionization source withmass separator and beam expander

Inside of clear room(GSS, UT)

outside of clear room(GSS, UT)

Air shower

Air shower

EU-Japan Joint Mercury Exploration Mission

0

2

4

6

8

10

0 500 1000 1500

55-keV_H^+_He^2+_He^+_N^+H^+He^2+He^+N^+

H^+

TOF-ch

0

2

4

6

8

10

12

14

0 500 1000 1500

110-keV_H^+_He^2+_He^+_N^+H^+He^2+He^+N^+

H^+

TOF-ch

Master Themes in Hongo of Univ. Tokyo• Construction and automation of ion/electron beam facility for

calibrating space plasma/particle instruments for BepiColomboMercury magnetosphere and future terrestrial/planetary explorations– 1 – 200 keV ion/electron beam line – Beam line profiling and calibration system control– Final calibration for BepiColombo high-energy ion sensor– A few eV – a few tens of keV ion beam line

• Design of suprathermal ion energy/mass spectrometers for future terrestrial/planetary explorations– Polar-ionosphere and Geospace explorations– Martian upper atmosphere and ionosphere exploration

• Data display/analysis system for auroral images and plasma particle data– Auroral imaging camera data from Reimei and ALIS– Google Earth or other visualization platform

Auroral emission and particle observations by ReimeiEmission-particle simultaneous measurements with high time/spatial resolutions

Launch August 23 in 2005 as piggy-back by a Dnepr rocketfrom the Baikonur Cosmodrome in Kazakhstan

Orbit Sun-synchronous

Inclination: 98.6 deg.

Meridian: 12:50 - 0:50 LT

Altitude: 610-670 km

Orbital period: 98.8 min.

Attitude Three-axis stabilized, sun-oriented (basically)

Telemetry S-band for up- and down-link from 1 to 133 kbps

Size/Weight 724×626×609 mm3 / 71.623 kg

Operation Extended to 2010 or later

Introduction of Reimei

Multi-Spectral AuroralImaging Camera (MAC)

Electron/Ion Energy Spectrum Analyzer (ESA/ISA)

Calibration of ESA/ISA

Development of MAC

Plasma Current Monitor(CRM)

Multi-spectral Auroral Camera(MAC)

Electron Spectrum Analyzer（ESA）

Ion Spectrum Analyzer（ISA）

Appearance of Reimei Movie of Aurora ImagesDecember 26, 2005

Ch.1 (427.8 nm) Ch.2 (557.7 nm) Ch.3 (670.0 nm)

70 km (64 bins)at 110-km altitude

70 k

m (6

4 bi

ns)

Exposure time: 60 msec.Exposure cycle: 120 msec.

Northward (Poleward)

Footprint of S/C mappedonto 110-km altitude along field line

10

1

0.1

0.01

Elec

tron

(0 –

60 d

eg.)

Ener

gy (k

eV)

Elec

tron

(60

–12

0 de

g.)

Ener

gy (k

eV)

Elec

tron

(120

-18

0 de

g.)

Ener

gy (k

eV)

10

1

0.1

0.0110

1

0.1

0.01UT(09:MM:SS) 10:40 10:45 10:50 10:55 11:00 11:05

ILAT 74.2 73.9 73.7 73.4 73.1 72.8MLT 0.9 0.8 0.8 0.8 0.8 0.8

Electron Energy-Time SpectrogramsDecember 28, 2005

Electron Energy-Time Spectrograms and Aurora ImagesDecember 26, 2005

UT(09:MM:SS) 10:40 10:45 10:50 10:55 11:00 11:05ILAT 74.2 73.9 73.7 73.4 73.1 72.8MLT 0.9 0.8 0.8 0.8 0.8 0.8

ALIS (Auroral Large Imaging System)

• Spectroscopic imaging system

• Absolute measurements

• 6 imager units• 6+4 fixed stations• 1 mobile station (bus)• Remote control• Campaigns• Free data on Internet

Detector units

• CCD detectors:1024x1024 pixels

• FOV: 60 or 90 degrees• Maximum resolution:

100 m at 100 km• Typical exposure time:

1-2 s• Typical temporal

resolution: 5 s• High sensitivity,

manages few Rayleigh

Shops and cafeterias in Hongo campus Near Hongo Campus of Univ. Tokyo

LIFE @ KOMABA LODGE

by Ting

Rent around 100 euro!!!!

Before move in

Desk & Bookshelf

Bed

Bathroom

Kitchenette 

wardrobe

Balcony

After … Cafeteria @ Komaba Campus

Transportation • 10mins

• Walking from HongoCampus of Univ. of Tokyo to Nezu Station

• 25mins• Subway from Nezu

Station to Yoyogi-Uehara Station without Line Change

• 15mins• Walk from Yoyogi-

Uehara Station to Komaba Lodge

Central business districtFashion forefront of

JapanKomaba Lodge Shibuya

20 mins walk

Sakura in Aprilcheerful cherry blossom season

All photos taken by Ting

And …..?

Shinjuku?Akihabara?

Ginza?

Check out by yourselves!

Let me know if you have any questionssazabi.li@gmail.com

Planetary Research (Astrobiology Laboratory)in Kashiwa Campus of Univ. Tokyo

Prof. Seiji SugitaE-mail: sugita@k.u-tokyo.ac.jp

URL: http://www.astrobio.k.u-tokyo.ac.jp/ Not much in English info yet…

We do laboratory experiments.

～25

km

Hongo CampusUniv. Tokyo

Kashiwa CampusUniv. Tokyo

Locations of Hongo Campus

andKashiwa Campus

of Univ. Tokyo

Kashiwa Campus

• Kashiwa Campus is north east of Tokyo. Let me honest with you. It’s in the middle of nowhere; not so close to nearest train station…

• But we have great research facility, an international lodge, and less air pollution. • It’s also cheap to live around here as well.

Train station

Kashiwa Campus

Kashiwa Campus

Cafeter

ia 2

Mon-Fri: 11

:00-20

:00

Sat: Lunch

only

Clinic

LibraryCafeteria 1

Food shop

Mon-Fri, 11:00-21:00

Our building

Mon-Fri, 11:00-20:00

◆ Instrumental developmentLaser-Induced Breakdown Spectroscopy (LIBS)

Nd:YAG laser Spectrometer

Vacuum ChamberEmission spectrum

◆High-speed impact processesExperimental facilities to study planetary evolution

Facilities to conduct high-speed impact experiments

Laser gun BBM LIBS system

• We study the early evolution of planets and satellites, and the origin of their atmospheres.

• We compare our Earth and other planets in order to understand why our Earth could harbor life.

Titan

Comets

Mars

Moon

Venus

Asteroids

Light-gas gun

Earth

Comparative Planetology

Research Interests Potential Research Topics•Impact Research

–Giant meteo impact causing Cretaceous-Tertiary dinosaur extinction

–The origin of life, particularly supply of organics to pre-biotic Earth

•Comparative Planetology–The origin of the Titan atmosphere–The subsurface structure of comet 9P/Tempel 1 using Deep Impact data

• Instrumental Development–Elemental analysis instrument (LIBS)

Potential Research Topics

Ejecta from Deep Impact

Titan atmosphere Polycarbonate impacting Cu at 6km/s

Projectile

Research Approaches

•Hypervelocity Impact experiments–Degassing experiments and chemical analysis–High-speed spectroscopy

• Instrument development–LIBS (laser-induced breakdown spectroscopy)–TOF MS (Time-of-flight mass spectrometer)

•Data analysis–Development of spectral data analysis algorithms.–Image and spectral analysis of mid-IR data from AKARI satellite and the Subaru telescope.

Research Approaches

2-stage light gas gun@ISAS Laser gun@Osaka Univ.

AKARI Satellite Subaru telescope

LIBS system@Kashiwa

Research Themesfor SpaceMaster Program

in Sagamihara of ISAS/JAXA

Hirobumi SaitoInstitute of Space and Astronautical Science (ISAS)

Japan Aerospace Exploration Agency (JAXA)(koubun@isas.jaxa.jp)

Institute of Space and Astronautical Science (ISAS),Japan Aerospace Exploration Agency (JAXA)

Main Island of Japan

Sagamihara

～30 km

Hongo CampusUniv. Tokyo

ISAS/JAXA

Institute of Space and Astronautical Science (ISAS),Japan Aerospace Exploration Agency (JAXA)

～30 km

ISAS/JAXA

ISAS/JAXA

ISAS/JAXA Institute of Space and Astronautical Science (ISAS),Japan Aerospace Exploration Agency (JAXA)

(http://www.isas.jaxa.jp/e/index.shtml)National Space Institutes in the world• US: NASA (National Aeronautics and Space Administration) • EU: ESA (European Space Agency)• Japan: JAXA (Japan Aerospace Exploration Agency)• Russia: RFSA (Russian Feredal Space Agency) / Roskosmos• China: CNSA (China National Space Administration)• Korea: KARI (Korean Aerospace Research Institute)• Taiwan: NSPO (National Space Organization)• India: ISRO (Indian Space Research Organization)• Canada: CSA (Canadian Space Agency)• Sweden: SNSB (Swedish National Space Board)• UK: BNSC, France: CNES, Germany: DLR, Italy: ASIBrazil: INPE

Research Themes for SpaceMaster ProgramHirobumi Saito Lab. at ISAS/JAXA

1. Automated Ground Operation System

for Micro Satellite REIMEI

2. Compensation Method of Satellite Fiber

Optical Gyroscope with “Shupe” Effect

3. GPS Receiver for Spinning Rocket

4. High Speed Data Communications for

Small Satellite

１．Automated Ground Operation System for Micro Satellite REIMEI

- We have operated micro satellite REIMEI from small tracking station at our laboratory.

- Scientists at remote area send their observation plans.

- At tracking station, plans are integrated and verified nearly automatically.

- At present we are constructing automatedsystem for satellite tracking.

Outline of INDEX (REIMEI)

160W (MAX)PowerTechnologyValidation

Engineering Mission

Aurora ObservationScienceMission

72 kgMass

72 x 62 x 62cm3Size

Outline of INDEX (REIMEI) Contd.

One Year PassedMission Life

Near Sun Synchronous(608 x 655 km)

Orbit24/8/2005, from BaikonurLaunch Date

$ ４ million + our salaryCost

Dnepr RocketLaunch Vehicle

- Three-Axis Controlledw/ Bias-Momentum

- Magnetic Control- Accuracy : 0.05deg

Attitude Control

ISAS/JAXA Sagamihara Campus Station• The station has an antenna of 3 meter

in diameter on the roof of the main building.

• Downlink: 131kbps* / Uplink: 1kbps• Orbit determination is based on:

– one-way doppler– TLE information– onboard GPS receiver (mission)

• The REIMEI operation team consists of young researchers, engineers, and students. Most operation software and tools are developed by themselves and a venture software house.>> Flexible operation!!!

*The onboard S-band transmitter (STX) is in the high-power mode. The mode is limitedly used when the satellite faces a critical situation.

Operation / Ground StationPhotos during the REIMEI operation

The REIMEI project has received a technical award from the Japan

society for aeronautical and space sciences in Jan., 2010.

2. Compensation Method of Satellite Fiber Optical Gyroscope with Shupe Effect

- Fiber optical gyroscopes (FOG) are suitablefor small satellite attitude control sensors.

- Bias angular rate of FOG due to temperaturevariation (“Shupe” effect) degrades FOG performances.

- We study on the compensation method of FOG “Shupe” effect by means of temporal measurement of temeperature.

FIBER OPTICAL GYRO with TEMPERATURE CONTROL

Commercial FOG(JAE JG-34)

Mass 1axis 140g Radiation 15 kradVibration 20GrmsShock 50G, 11msBias Stability is Critical

0.1[deg/h] with temp. cntl.

Measurement System of FOG Bias Rate due to “Shupe” Effects

3. GPS Receiver for Spinning Rocket

- GPS receivers for spinning rocket are

developed with antenna diversity techniques.

- Software receiver algorithm is proposed and

investigated by means of simulations.

- The algorithm will be implemented in the GPS

hardware.

Background• Cost effective GPS receivers for the

next-generation solid motor launchers and sounding rockets of ISAS/JAXA– Precise payload insertion– Redundant flight safety

©JAXA

Open Source GPS Receiver

Total Price<$200

• Originally designed by Clifford Kelly and released under GNU Public License (GPL)

• Ported to ARM7-based GPS baseband processor （Zarlink GP4020） and running on NovAtel SuperStar II

High-Dynamic Flights • Frequency lock loop (FLL) provides

robust signal tracking • Successful flights on several high power

model rocket missions

Dual Antenna Software-Defined GPS Receiver

Digitized GPS signal data will be transferred to the host PC via USB 2.0 and post-processed by a software-defined GPS receiver

Multi-Antenna Receiver Development

Namuru II L1/L2C receiver with reconfigurable FPGA core

©General Dynamics

©SpaceLink

Quad-antenna receiver using GP4020-compatible GPS correlator chipsets

4. High Speed Data Communicationsfor Micro Satellite

- The graduate school of technology in the University of Tokyo plans to develop micro satellite with 50kg for earth image monitoring.

- Besides imaging sensors, high data transmissions are a key technology.

- We plan to develop high data transmissiontechnology.

- On-board instruments should be compact and low-power consuming for matching micro satellite.

- Ground demodulation should be sophisticated, using error correcting code and equalization techniques.

High Speed Data Communications for Small Satellite

Conventional System for Large Satellite

Advanced System for Small Satellite

Satellite has to transmit clear waves receivable at any ground stations.

Satellite can transmit somewhatwarped/peculiar waves becauseground station can correct them.Electrical Control

of Beam Directionby Phased Array System

Mechanical Control

of Antenna Direction

低電力高速

RF Measurement Instruments for Space Communications

Software Simulation System for RF Communications

Accommodation at ISAS/JAXA

• http://www.isas.jaxa.jp/e/index.shtml• http://www.isas.jaxa.jp/e/researchers/accommodation/index.shtml

Air conditioner, TV, small refrigerator, desk/chair, bed with linens, toilet and shower with small bathtub in 15 m2

• Common kitchen, clothes mashers/ driers available anytime

• Cafeteria open for lunch at weekday

• Shop open for 9:30-16:30 at weekday

Interview through skype or TV conference system using internet

Before mutual decision/agreement to study together in Japan for master thesis subject, a remote interview between SpaceMaster students and Japanese groups is preferable.

Please contact to Masa Hirahara and the professor by whom you wish to be supervised via email.

1. Masa Hirahara (Space Physics in Hongo of Univ. Tokyo)email: hirahara@eps.s.u-tokyoskype: masa.hirahara

2. Seiji Sugita (Planetary Research in Kashiwa of Univ. Tokyo)email: sugita@k.u-tokyo.ac.jp

3. Hirobumi Saito (Satellite Subsystem in Sagamihara of ISAS/JAXA)email: koubun@isas.jaxa.jp