Program and planning at ISAS/JAXA space science

The 50th anniversary of the Space Research Institute Russian Academy of Sciences HQ, 30 Sep. – 2 Oct. 2015

Saku Tsuneta Institute of Space and Astronautical Science

Japan Aerospace Exploration Agency

http://www.iki.rssi.ru/eng/iki50.htm

Introduction of ISAS/JAXA • As a national center of space science & engineering

research, ISAS carries out development (including vehicle development), launch and in-orbit operation of space science missions (scientific satellites, probes, sounding rockets, balloons and instruments on ISS).

• As an inter-university research institute, these activities are intimately carried out with universities and research institutes inside and outside Japan.

• ISAS always seeks for international collaborations. • Bottom-up process for mission selection: Space science

missions proposed by researchers are reviewed and incubated by ISAS.

• ISAS is in a process of major reform for sustainable excellence as a part of JAXA.

Technology driven Leads and creates space

science programs

Science driven Stimulates and encourages

new technology development

ISAS uniqueness#1: Close ties between space science and space technology

Space Science Divisions Space Astronomy Astrophysics

Solar System Science Interdisciplinary Space Science

Space Technology Divisions Space Flight Systems

Spacecraft Engineering

Recent accomplishments HAYABUSA & IKAROS

[Tech. Demo. #1] Solar sail deployment

[Tech. Demo. #3] Photon propulsion

[Tech. Demo. #4] Solar sail guidance, navigation and control

Launch (21/May/2010)

Venus Flyby (8/Dec/2010)

[Tech. Demo. #2] Power generation by sail-mounted thin film solar cells

Extended operation phase (Jan/2010 - now)

～9/June/2010

～10/June/2010

Nominal operation phase

(May/2010 - Jan/2010)

IKAROS Technology Demonstration of Interplanetary Solar Power Sail

Thin film solar cell

Solar sail Diagonal 20m

2003 HAYABUSA-1 2014 HAYABUSA-2 2022 Phobos/ Deimos SR

Various missions related to sample return and/or atmospheric-entry are being discussed and proposed.

Phobos/Deimos SR Trojan SR with Solarsail Mars EDL mission

Deployable Aeroshell w/U. Tokyo

HTV-R capsule(JAXA)

Systems for 12km/s (Mpeak=40) reentry speed

Thermal durability and response in high aerodynamics heating environment are evaluated with various materials in ISAS arc wind tunnel.

ISAS uniqueness #2: Close ties between ISAS and universities

• Strong connection with – Graduate University for Advanced Studies – University of Tokyo – Other universities

• Approx. 200 resident students • Produce annually approx. 20 PhD and 60 MSc • Provide hands-on education/training for space science

and engineering • Provide access to big space programs and smaller

balloon & sounding rocket projects

HAYABUSA 2003-2010 Asteroid Explorer

AKARI(ASTRO-F)2006-2011 Infrared Astronomy

KAGUYA（SELENE)2007-2009 Lunar Exploration

SUZAKU(ASTRO-E2)2005- X-Ray Astronomy

M-V Rocket

AKATSUKI 2010- Venus Meteorogy

Hisaki 2013 Planetary atmosphere

HINODE(SOLAR-B)2006- Solar Observation

IKAROS 2010 Solar Sail

JAXA recent science missions

HAYABUSA2 2014-2020 Asteroid Explorer

Fiscal Year 2008 2009 2010 2011 2012 2013 2014 2015 2016 2017 2018 2019 2020 2021 2022

Operating / C

oncluded

Under D

evelopment S

ounding

B

eing considered

R

ocket

ASTRO-EII（SUZAKU）’05

GEOTAIL’92

SOLAR-B（HINODE）’06

MUSES-C（HAYABUSA）’03

ASTRO-H ’15

ASTRO-H

HAYABUSA SUZAKU

HINODE

Daytime Dynamo ’11,’13 ▼ ▼ CLASP ’15 ▼

MMS ’14 ▼

Space Science Cooperation with NASA and ESA

ASTRO-F（AKARI）’05

PLANET-C（AKATSUKI） ’10

BepiColombo ’16

SPICA ’27-28

JUICE ’22

▼

SPICA

Bepi Colombo

cooperation with NASA cooperation with ESA

HAYABUSA2 ’14 ▼

▼

▼

▼

▼

ISAS/NAOJ-NASA-UK-ESA Hinode

0 50 100 150 200 250 300

JapanUSA

UKNorway

SpainFrance

ItalyBelgium

GermanyIrelandCzechChinaIndia

KoreaRussiaAustria

AustraliaNetherlands

GreeceSlovakia

BrazilSwitzlandSweeden

IranColombia

LatviaArgentina

グラフ タイトル

2007

2008

2009

2010

2011

2012

2013

2014

2015

Hinode refereed papers: 842 papers for 9 years Immediate release of just-taken data

with analysis software & latest calibration info.

p Approx.100 papers per year p Data used by 23 countries p Top US, Second Japan, third UK p One-third of papers come from US p Same contribution from Asia, US, Europe

Curator: Dr. Shimojo (NAOJ)

Whole Asia

Whole Europe

Itokawa S-type asteriod falcon

hayabusa

Led by JAXA Lunar & Planetary Exploration Program Group

ISAS/JAXA Astromaterials Science Research Center

LL chondrite

Parent body (>20 km) formation

Thermal metamorphism 4.562 Gyr ago

Catastrophic destruction (Large-

scale collision)

Reaccumulation

Formation of Itokawa Rubble-pile

Micro meteorite

Solar wind Cosmic ray

Space weathering

Resurfacing (～10’s cm/My)

regolith gardening (150 y -3 My)

Astonishing pieces of information Derived from 30-micron sample!

falcon

hayabusa

Planetesimal

Hayabusa 2 mission

1/5

falcon

hayabusa

JAXA Hayabusa2 vs NASA OSIRIS-REx

ISAS/JAXA HAYABUSA2 mission • Launched: 2014, arrival:2018, departure: 2019,

return: 2020 • Target: 1999 JU3 C-type asteroid NASA OSIRIS-Rex mission • Launch: 2016, arrival:2018, departure: 2021, return: 2023 • Target: 101955 BENNU D-type asteroid

Launch Dec.3, 2014

Earth Swing-by Dec.3, 2015

Asteroid (1999JU3) Arrival Jun.-Jul. 2018

Earth Return Dec. 2020

Hayabusa2 Mission Outline

•asteroid remote sensing •small rovers and lander release •multiple samplings

Departure Dec. 2019

Impactor release

sampling from artificial crater

Crater forming

Hayabusa2 Current Status

Sun Launch (Dec. 3, 2014)

Earth swing-by (Dec. 2015)

1999 JU3 arrival (Jul. 2018)

1999 JU3 orbit

Hayabusa2 trajectory

Earth orbit

We are here! (Oct. 1,2015)

• Launched by H2A on Dec.3, 2014. • Commissioning phase completed on Mar.

2, 2015. • 524hr of the ion engine powered cruise

completed to be ready for the Earth gravity assist.

• Earth gravity assist on Dec.3, 2015.

μ10 Ion Engine

Deployed Sampler horn

Launch from Tanegashima

Earth to asteroid trajectory

Alt.20km

Alt.100m

Alt.30m

Alt.0m

Reference Path

True Path

①Leaving HP. Starting GCP-NAV (Ground/Onboard Hybrid Navigation)

②Entering Autonomous Mode

③Deploying Target Marker

④Aligning Attitude to Local Surface

⑤Touch Down

⑥Escape ΔV

18

Touch Down & Sampling Operation Sequence

“GCP” Landmark based navigation

ONC LIDAR

Target Markers & FLASH

LRF

The First Interplanetary Micro-Spacecraft

PROCYON Launched on Dec 3rd, 2014

Development

Spacecraft-System Weight 65 kg Size 550 mm×550 mm×670 mm Components Power SAP×4 Attitude RW×4, NSAS×5, FOG×3, STT×1 Communication XTRP (X-Band Transponder), GaN SSPA (Soid State Power Amplifier) VLBITX (Tone Signal Generator for VLBI Navigation) Propulsion Ion Thruster×1 (for Deep Space Maneuver) Cold-Gas Thruster×8 (for Reaction Control System and Trajectory Correction Maneuver) Mission Telescope×2 (for Asteroid Observation and Geocorona Observation)

Mission

Achievements Demonstration of 50 kg-Class Deep Space Exploration Micro-Spacecraft Bus System Success Miniature Ion Thruster and Cold-Gas Thrusters System Success High-Effieciency GaN SSPA Success VLBI Navigation Technology Success Geocorona Observation Success

Address : funase@space.t.u-tokyo.ac.jp (Ryu FUNASE)

The University of Tokyo and JAXA

Demonstration of 50 kg-Class Deep Space Exploration Micro-Spacecraft Bus System Miniature Ion Thruster and Cold-Gas Thrusters System High-Effieciency GaN SSPA VLBI Navigation Technology Geocorona Observation Close Flyby Observation of Near Earth Asteroid

CG by Go MIyazaki

Epsilon H-II B H-II A • First Flight in 2001 • 27 successful launches/28 • Latest one: government • GTO 4-6 ton class capability

• First Flight in 2009 • 4 successful flights/4 of 16.5 ton HTV to ISS • GTO 8 ton class capability

• 1 successful launch/1 • 3 stages Solid Rocket • LEO 1.2 ton

SSO 0.45 ton

JAXA Launch Vehicles To be replaced with H3 in 2020

Launch capability being improved

New Medium-sized Satellite Program

• Epsilon Launch Vehicle is a solid propellant rocket capable of launching a satellite weighing 600kg into SSO.

• With standardized s/c bus, ISAS intend to implement low-cost, high-cadence focused missions.

Launch of Hisaki

22

Hisaki Successfully launched on 14 Sep. 2013 by the Epsilon launch vehicle EUV spectrograph for dedicated planetary observations (Venus, Mars, Jupiter, Mercury, Saturn) S/C weight：340kg

S/C power：900W S/C size: 7m x 4m x 1m Orbit：950～1150km λ：50-150nm (EUV)

Hisaki Successfully launched on 14 Sep. 2013 by the Epsilon launch vehicle EUV spectrograph for dedicated planetary observations (Venus, Mars, Jupiter, Mercury, Saturn) S/C weight：340kg

S/C power：900W S/C size: 7m x 4m x 1m Orbit：950～1150km λ：50-150nm (EUV)

Erosion?

Habitable Mars Non-habitable Mars

Hisaki challenges the observation of the comet 67P/Churyumov–Gerasimenko this month. Oxygen atom emission is detected with a exposure time of 1.3days (under analysis).

Observation of Comet 67P

←↑ Raw data

Venus orbiter Akatsuki • Objective: Understanding the

atmospheric dynamics and cloud physics of Venus

• Science instruments – 1mm Camera (IR1) – 2mm Camera (IR2) – Longwave IR Camera (LIR) – Ultraviolet Imager (UVI) – Lightning and Airglow Camera (LAC) – Ultra-stable oscillator (USO)

• Launched in May 2010 • Current status

– The Venus orbit insertion failed on Dec 7, 2010 due to malfunction of main engine.

– Another orbit insertion maneuver will be conducted in Dec. 2015 using small attitude control thrusters. 3-D observation of

atmosphere from Venus orbit

Equatorial orbit (S/C 500 kg, Payload: 35 kg)

AKATSUKI(PLANET-C) – 2010- Venus Meteorogy ESA Bepi-Colombo 2017

ERG 2015- Van Allen belt

ERG 2016 Van Allen belt

M-V Rocket

HAYABUSA2 2014 Asteroid sample&return

SPICA 2025- Infrared Astronomy

ASTRO-H 2016 X-Ray Astronomy

ESA JUICE 2024 Jupiter Icy moons

High-cadence Low-cost

focused missions 2022, 2024….

ESA JUICE 2022 Jupiter Icy moons

JAXA missions under development

SPICA 2027 IR Astronomy

SLIM 2020 Moon landing

Phobos/Deimos Sample Return 2022

LiteBird 2025 CMB polarization (notional)

SLIM

ISAS/JAXA mission categories

Strategic Large Missions (300M$ class) for JAXA-led flagship science mission with HIIA vehicle (3 in ten years)

Space Policy Commission under cabinet office intends to guarantee predetermined steady

annual budget for space science and exploration to maintain its scientific activities

Competitively-chosen medium-sized focused missions (<150M$ class) with Epsilon rocket (every 2 year)

Missions of opportunity (10M$ per year) for foreign agency-led mission, sounding rocket, ISS

SPICA

JUICE

#4, #5 AO

ERG

Phobos/Deimos LiteBird (preliminary)

ATHENA

2010 2020 2030

Hisaki(2013)

SPICA (2027-28)

Future ISAS science missions

BepiColombo (ESA, 2016)

SLIM(2020) #4 (2022) #5(2024)

ERG (2016)

Astro-H (2016)

JUICE (ESA, 2022)

ATHENA(ESA, 2028) WFIRST(NASA, 2025)

Strategic L-class (3 missions /10 yrs) w/ HII-A and H3

Competitive M-class (1 mission/2 yrs) w/ Epsilon

S-class Foreign agency-led mission

Phobos/Deimos (2022) LiteBird (2025) preliminary

ISAS Astrophysics and fundamental physics 2020s Lead cryogenic astrophysics missions

30

Hot and Energetic Universe

Reds

hift

(z)

Wavelength (m) 10-12-10-8 m 10-5-10-4 m 10-3-10-2 m

z=0.5

z=3

z>>10

Galaxy Evolution Formation of Solar Systems

SPICA(ESA-led)

ATHENA(ESA-led)

Cosmic Microwave Background and Inflation

(X-ray) (IR) (Milli-wave)

LiteBIRD (JAXA-led) under assessment

SPICA Large Cooled Space Telescope for Mid-IR/Far-IR astronomy

SPICA: Space Infrared Telescope for Cosmology and Astrophysics

Telescope: 2.5 m, <8K Wavelength: 12–230micron

Scientific Purpose: To elucidate processes in the enrichment of the Universe with metal and dust, leading to the formation of habitable worlds.

H2O ice

Calcite CaCO3

Dolomite CaMg(CO3)2

20 40 60 mm

Olivine (Mg,Fe)2SiO4

Pyroxene (Mg,Fe)SiO3

20 40 60 mm

SPICA will detect zodiacal disk analogues and their IR spectra which contain key information on their thermal histories reflecting formation of solar/planetary systems.

High-temperature minerals

Low-temperature minerals formed by aqueous mineral alteration or alternate process

Changes of mineral and ice properties in debris disks

Debris Disks/Rings

Zodiacal Dust Kuiper Belt Dust

Thermal History?

Dust evolution in planet-forming disks to solar system analogues

ISAS Engineering: Small lunar-lander (SLIM) for pinpoint landing technology

demonstration

• Technology demonstration with Small Spacecraft • Image-based Navigation utilizing Lunar Terrain • Autonomous Obstacle Detection • Robust Pin-point Guidance • Landing Shock Absorber • High-performance Propulsion • Exploration using Tiny Rovers (option)

• Frequent trials of lunar/planetary surface exploration technology • Precursor of future full-scale lunar or planetary missions

SLIM (Smart Lander for Investigation of the Moon)

SLIM is a mission to demonstrate the technology for pin-point soft landing on lunar or planetary surface.

The 3rd Small Satellite Mission: proceeding to implementation phase

34

BepiColombo MMO(ESA-led)

Phobos/Deimos Sample Return (JAXA-led)

Asteroid Sample Return Hayabusa, Hayabusa2 (JAXA-led)

JUICE (ESA -led)

35

SLIM Moon landing (JAXA-led)

ISAS Planetary science 2020s Lead sample & return

36

ISAS/JAXA Phobos or Deimos Sample Return

Science case • Reveal the origin of a Mars moon (Phobos

or Deimos): (A) Captured D-type asteroid, or (B) piled fragments by a giant impact • Only sample analysis will give the end to

the ever-lasting-argument. • Be it (A) or (B), there are subsequent steps

in the sample analysis that will decipher rich information on the planet.

• Being in close proximity of the planet, the moons are showered by impact-ejected ancient Mars surface material: A possible channel to decipher the Mars surface transition via sample analysis.

System Design ongoing (Chemical – Electric Case)

Launch in 2022, Return in 2027 Outward: chemical propulsion Homeward: electric propulsion Launch Mass : 2300kg Two stage modules: Exploration & return: 900kg Chemical propulsion : 1400kg

① Mars arrival

② Quasi-orbit #1

③ Descent #1

④ Landing #1

⑤ Ascent #1

⑥ Quasi-orbit #2

⑦ Descent #2

⑧ Landing #2

⑨ Ascent #2

⑩ Quasi-orbit #3

⑪ Mars departure

Mission Profile Example in the Proximity of Martian Moon

System Design & Engineering Challenges

• A Round Trip to a Martian System • Proximity Operation around a Martian Moon • Sample Retrieval Mechanism

Summary • We do complex international collaboration for

the sake of the maximum science. • International collaboration is essential for JAXA-

led L and M class missions . ISAS/JAXA is eager to participate in large missions led by foreign agencies that JAXA cannot afford.

• Similar missions are usually proposed to other space agencies almost simultaneously, meaning redundant pursuit. Early and careful agency-level dialog is important not to kill a science discipline in one sector of the world and not to waste young people’s efforts.