1. The ILOA Galaxy Forum Europe 2013
Solar System Exploration:
A Review of the Hayabusa and
IKAROS Missions
April 5, 2013
International Space University Strasbourg Campus,
Strasbourg, France
Hajime YANO 1,2,3,4)
1) Institute of Space and Astronautical Science (ISAS), JAXA, Kanagawa, Japan
2) JAXA Space Exploration Center (JSPEC), JAXA, Kanagawa, Japan
3) Graduate University for Advanced Studies (SOKENDAI), Kanagawa, Japan
4) Graduate School of System Design Management, Keio University, Kanagawa, Japan
Frontier!
(Copyright: Gary Larson)
1

2. Technology Goal: Deep Space Port and Round-Trip
Explorations, a Blue Print of JAXA Long-Term Vision
Heliocentric 1(AU) 1.01(AU) 1.5(AU) 2~4(AU) 5.2(AU)
Trojans
Deep Space Port
（Sun-Earth L2）
Lunar Base Jovian
Asteroid
Mars Belt System
Earth
LEO Port
LEO
Observatories
Further
Deep
Space
L2
NEOs
Observatories
Hayabusa
(Courtesy: JAXA, A. Ikeshita, AAAS)
Earth Swing-by IES & Optical Navigation Touchdown for Sampling Earth Direct Re-entry Sample Return
Western side “Body” side
10m
Eastern side “Head” side
2

3. Main Belt Asteroids, Dwarf Planet, Moon and Earth:
Comparison by Size
Earth
Moon
Dwarf Planet
Main Belt Asteroids
(G~C?) (V)
1 Ceres 4 Vesta 21 Lutetia
974 x 908 km 578×560×458 km 132×101×76 km
HST  Dawn HST  Dawn Rosetta
Asteroids and Comets Visited So Far: Martian Satellites
Comparison by Size and Spectral Types
Koronis Family (C?)
(S) Phobos:
26.8 × 22.4 × 18.4 km
(S)
Mars (C?)
Crosser Deimos
(Q) (S) (E)
15 × 12.2 × 10.4 km
Near Earth Objects
(S)
(S)
(Collage
Courtesy:
E. Lakdawalla,
TPS, 2010)
Main Belt Asteroids Cometary
Nucleus
(M or C)
(C) (S)
3

4. Near Earth Asteroid Itokawa:
Comparison to a Terrestrial Landmark
224 m
142 m
Ground Light Curve Model Ground Radar Model
Kaasalainen, et al (2002.) Ostro et al.(2004)
Chelyabinsk Event and 2012 DA14 Flyby
4

5. Extraterrestrial Material Accumulation Rate:
~100t per Day Average, Even Now
Zodiacal Light 1999 Leonid Meteor Strom
（ｃ） Yano, NHK, Nakanishi
（ｃ） M. Ishiguro, et al.
Minor Bodies as Ingredients of Planets and Life
Habitable
Meteorites & Minor Bodies Planets Environment
Cosmic Dust
Rocks and
Metals
S-type Asteroids Terrestrial
Ordinary
Atmosphere
Chondritres
C,D,P-type Ocean
Carbonaceous Gaseous
Chondritres Asteroids
Water,
Organics Land
IDPs
Comet Nucleus Icy
5

6. Hayabusa in 2003-10:
Challenge to the First Asteroid Sample Return
•Launch: May 9th, 2003
•Earth Gravity Assist:
May 19th, 2004
•Itokawa Rendezvous:
September 12th, 2005
•Sampling and Landing:
November 19th and 25th, 2005
•Asteroid Departure:
April 25th, 2007
•Earth Return: June 2010
Cost: ~180M US$
including s/c, launcher, & operation
Hayabusa: To Establish Technologies for Deep
Space Round-Trip Explorations
(1) Ion engine system for
interplanetary cruise
(e.g., Deep Space-1)
(2) Autonomous navigation and
control by image processing
(e.g., Deep Impact)
(3) Surface sample collection from
a microgravity body
(e.g., OSIRIS)
(4) Direct Earth re-entry from
interplanetary space
(e.g., Genesis & Stardust)
Size: 1.6 x 1.1 x 1.0 (m); Mass: 510kg(wet)
6

7. Orbits of Hayabusa and Itokawa
Itokawa
Itokawa
Earth
Rendezvous Earth Orbit Crossing
(2005/09) Sun
Sun
Earth
Launch Asteroid Departure
(2003/05) (2007/02)
Earth Swing-by Earth Return
(2004/05) (2010/06)
From Launch to Rendezvous Earth Return Trajectory
• Itokawa is a potentially hazardous asteroid, which intersects
Earth’s heliocentric orbit
• Hayabusa follows the asteroid during the rendezvous phase
7

8. Alignments and Footprint Overlaps
among the On-board Instruments
( M. Abe at al., XXXVII LPSC, (2006))
Hayabusa’s Tough & Go
Gate Position (2005/09/12~09/27)
Home Position (09/27~10/05)
Science Tour (10/05~10/21)
Site Selection (10/28)
Touch Downs (2 Rehearsals, 1 Image Navigation Test & 2 TDs)
(11/04, 09, 12, 19, 25)
8

9. Landing Sites at the Muses-C Regio
TD1
TM
TD2
TD1 = MUSES-C Regio High Altitude Region
Sample Catcher： Room B
TD2 = Equatorial MUSES-C Regio at the Edge of Shirakami Cliff
Sample Catcher： Room A
(The 2011 Science Special Issue based on the samples from here)
(Yano, et al., MAPS, in prep.)
＜Retrieval, Transport,
Landing of the ERC at Woomera in Cleaning, Storing, Purging＞ ＜Soil Sampling＞
Australia in June 14, 2010
＜International Witness＞
＜Arrival to Curation Facility＞
＜XCT Scanning＞
9

10. Initial Analysis by the HASPET in 2010-11
Science Predicts Unknowns by Applying Nature’s Laws
that Are Applicable to Any Places at Any Time: (e.g.)
Itokawa’s Color and Albedo Heterogeneity
Western side “Body” side 10m
Eastern side “Head” side
(Saito, et al., Science (2006))
• No previously observed asteroid bodies show large variations
in both color and albedo.
• Correlations between color and albedo on Itokawa can be found.
• Generally, the brighter area is bluer, while the darker is redder.
Cf. Space weathering evidence at landslides on Eros
10

11. Most Surfaces Indicate Similar Minerals at Larger Scale
* Spectra of three typical regions are different each other in the depth of the 1-micron band. This disagreement is a result of
different grain size as well as degrees of space weathering. (M.Abe, et al., Science (2006))
Ultra-microtoming TEM Analysis Answered the Asteroid-
Meteorite Paradox with Space Weathering Evidence
(Noguchi, et al., Science, 2011)
Nano-phase iron particles on the
top exterior of the individual
particle
11

12. Rough Terrain Close-Ups
* Bright patches are evident
on darkened, monolithic
boulders, implying brittle
target impact craters as well
as scratches by pebble
mobility (Miyamoto, Yano, et al., Science, 2007)
Smooth Terrain Comparison:
Itokawa vs. Eros in the Same Scale
Little Woomera Muses-C Regio Eros pond
(Miyamoto, Yano, et al., Science, 2007)
12

13. Touch Down Site Close-Ups :
ONC-T Descent Images (V-band)
Discovery of Gravel Field at the Gravitational Low and
Evidence of Granular Mobility in the Microgravity
•Spatial Resolutions: 6~8
mm/pixel (cf. NEAR: 12 mm/px)
•Densely filled with size-sorted
(mm-cm) pebbles of similar
brightness
(Signs of flow along potential slope and possible seismic shaking:)
(Yano, et al., Science (2006))
X-ray Tomography of 3D Internal Structure of
Asteroid Regolith
(Tsuchiyama, et al., Science, 2011)
13

14. Terrestrial Geological Features:
Governed by Gravity, Heat, Air and Water
Boulder Terrain Gravel Field
Landslides Sand Pond Breccia
Asteroidal Geological Features: Mainly due to
Impacts and Vibrations in Vacuum and Microgravity
Boulder Terrain Gravel Field
(Itokawa) (Itokawa)
Landslides Fine Regolith Pond Breccia
(Eros) (Eros) (Itokawa)
How to form apparently similar geological features to the Earth?
What these similarities and differences tell us about asteroid evolution?
14

15. Image-Model Comparison of
Granular Flow and Surface Potential on Itokawa
* Images indicating directions of surface
mobility © Univ. Tokyo, JAXA/ISAS
Univ. Aizu, Kobe Univ., PSI,
Univ. Michigan
Miyamoto, Yano, et al.,
Science (2007)
* Potential vectors match with granular flow images
Gravity-Duration Diagram for the Microgravity Geology
Experimental Facilities
**** Long
Day-Year
22wk~1yr
wk~1 yr
(10-3 ~ 10)
-5
(10-３ ~ 10 -5) ISS Gardening,
1~2 wks Granular
Soyuz Retrievable Free Flyers Convection,
(10-3 ~ 10-4)
1 wk~1 yr Re-accumulation of
(10-4 ~ 10-6) Ejecta
Expendable Brazil Nuts Effect
Min.
Sub-Orbital Sounding Rockets
Reusable
M 3~5 min.
(10-3 ~ 10-4)
5-10 min.
(10-4 ~ 10-5)
Dust Aggregate
Granular Surface
i Parabolic Flights
Balloon Capsule Mobility
Sec.
~30 sec.(10-4)
n 20~30 sec.
(1/4 ~ 10-2)
Catapult-mode
Drop Tower Non-G Effect,
4.5-9 sec(10-5) Dust Levitation
. Small Tower
2 sec(10-3) Hypervelocity Impacts
10-0 10-1 Short
Gravity Level (G)
（Micro-G
Geological
Phenomena）
1999JU3
Itokawa
Enceladus
Earth
Moon
Ceres, Vesta
Mars
Human-Tended Unmanned
* Plus counter-mass/low friction stages and underwater analog sites for longer duration
15

16. Past, Present and Future of Asteroid Itokawa
Revealed by In-situ Observation and Sample Analysis
Planetesimals Catastrophic Disruption
Formation of Itokawa s Thermal Alteration
Parent Body (> 10 km) of the Interior
(< 4562Ma)
Surface Mass Loss (10 s cm/My) Micrometeoroid Solar Wind Re-accumulation
Impacts Galactic
Cosmic Rays
Formation of Itokawa as
a rubble pile asteroid
Space Weathering
Granular Mobility/
Convection (100y ~ 1My)
Present Hayabusa-2 in 2014-20:
Carbonaceous Asteroid Sample Return and Internal Structure Study
<Major Characteristics>
・The first rendezvous and sample return of a C-
type asteroid (1999 JU3)
・The spacecraft system design has a direct
heritage and lessons from Hayabusa-1 with
an impactor
<Scientific Objectives>
(1) Material distribution map at the Main
Asteroid Belt
(2) Chemical evolution of water and organic
material (Life precursors)
(3) Internal structure and evolution process of
highly porous primitive bodies
OSIRIS-Rex
NASA New Frontier Class
1999 RQ36 (B type) SR
in 2016-22
16

17. Near Earth Objects: Itokawa vs. 1999 JU3 at a Glance
Earth Crossing Orbits
Itokawa
Mars
Earth
1999 JU3
(162723) 1999 JU3
(C) (25143) Itokawa (Collage
International
(S) Courtesy:
Space
P.Station
Lee, 2006)
(Model Courtesy:
Kaasalainen, et al., 2008)
(Collage Courtesy:
~980 m P. Lee, 2006)
“Chicks” of Hayabusa:
Sample Return Missions to sub-km~km Sized Bodies
Post Hayabusa Series
Hayabusa Hayabusa-2 Hayabusa Mk-II
Itokawa = S type 1999 JU3 = C type D type, Dormant comet
(1996~/2003-10) Lessons Learned from Hayabusa Advanced, Full Model-change
(2011~/2014-20) (Mid 2010’s~/Early 2020’s)
OSIRIS-REx
1999 RQ36 = B type
New Frontier Class
Carbonaceous (2016-23)
Chondrites
Ordinary
Chondrites
IDP,
AMMs,
C type Tagish
Marco Polo-R Lake?
S type
D type 1999 FG3 = C type
Cosmic Vision-M
Main Asteroid Belt (2022-29) 34
17

18. Technology Goal: Deep Space Port and Round-Trip
Explorations, a Blue Print of JAXA Long-Term Vision
Heliocentric 1(AU) 1.01(AU) 1.5(AU) 2~4(AU) 5.2(AU)
Trojans
Deep Space Port
（Sun-Earth L2）
Lunar Base Jovian
Asteroid
Mars Belt System
Earth
LEO Port
LEO
Observatories
Further
Deep
Space
L2
NEOs
Observatories
IKAROS
IKAROS
Venus
Earth
Helios-1 Sun
36
Galileo
(Courtesy: Dermott, et al.)
18

19. Acquiring Outer Planet Exploration Capability:
Development History of the Solar Power Sail in Japan
2003. August
Balloon Test(B30-71) at 36km alt.:
Active Deployment of Sail (4m)
2004. August
Sounding Rocket(S310-34) at >100km alt.:
Active Deployment of Sail (10m)
Modeling of Sail Dynamics
2006. September
M-V-7 Rocket Sub-payload (SSSAT) in LEO:
Deployment Demo of Small Power Sail (5m)
2010. May
H-IIA-17 Piggy-back (IKAROS) in deep space:
First Solar Sail in Interplanetary Space
Deployment of Sail Membrane (200 m^2)
Early 2020’s
Solar Power Sail (3000 m^2) with Ion Engines:
Cruising Science (IR astronomy, High energy
astrophysics, Dust) and Jupiter and Trojan
explorations
IKAROS in 2010-2013
The first Interplanetary Demo of Solar Sail Technology
• May 21, 2010 Launched by H-IIA-17
• June 3-10, 2010 Sail deployment and produced power from ultra-thin solar cells on the sail
• June 23, 2010~ ALADDIN started its dust measurements
H-IIA-17 Launch • July 9, 2010 Orbital determination by RARR confirmed solar radiation acceleration
• Dec. 6, 2010 Venus flyby and the extended mission started
・ May 2011 First round trip to complete at aphelion
・ Oct. 2011 Last ALADDIN data down-linked (All Images Courtesy: JAXA)
・ Dec. 2011 The first hibernation period started
. Sep. 2012 IKAROS resumed communication link again and ⑤ Visual Confirmation
ALADDIN-E powered on
. Oct. 2012 The second hibernation period started
① ③ ④
②
Venus Fly-by
First stage
(Statically)
Second Stage
Two-Step Sail Deployment
(Dynamically)
IKAROS Completed Its Nominal Operation with Full Success in
2010-11 and Continues Its Extended Operation to 2012 and Beyond.
19

20. Acceleration by Solar Radiation Pressure
(Data on 2010/06/09 UTC)
Increased Velocity [mm/s]
The Second Stage Sail Deployment
Lack of Velocity data due to
the Deployment Operation
Achieved Solar Radiation Propulsion（＝0.1g） as Estimated
 The World’s first solar sail was finally born!
20

21. IKAROS-ALLADIN System
ALDN-S （37g in total）
ALDN-S-1 (Anti-Sun Face)
Substrate 9 micron-
ALDN-S-4
thick PVDF
Substrate
Sun Face ALDN-S-1
PVDF Sensor-L
Sensors PVDF Sensor-S
80x100mm(9μm) 250x500mm
(20μm)
20 micron-
think PVDF
ALDN-E (210 g)
ALDN-S-3
IKAROS ALDN-S-2
Substrate Spacecraft
Substrate
ALDN-E Electric component
30x100x112mm
ALDN-S
ALDN-E
SAIL-I/F
LVDS
1W
PVDF 8ch +5V,GND,-5V
IKAROS Trajectory and
Earth’s Circumsolar Dust Ring and Blob
(Reach, et al., Icarus, 2010)
Venus Flyby
21

22. Earth’s Circumsolar Dust Crossing
for the Inbound and Outbound Trajectories
NOTE: Attitude factor correction of the ALADDIN pointing face
with respect to the solar and apex angles must still be made
Plan Solar Power Sail for Jupiter-Trojan
Exploration in Early 2020’s
Synergy with JUICE Challenge to Jupiter System
Condition of the Jovian System
Formation and Evolution
Trojans Galilean Satellites Jovian
System Mechanism Magnetosphere
22

23. ConceptEnceladus Ocean Ice Plume
Sample Return in 2020’s to Later
Searching for “Neighbors” in a Present Ocean
Lessons Learned from Hayabusa (1):
Expect the Unexpected
23

24. Lessons Learned from Hayabusa (2):
Know Your Enemy
Ground Light Curve Model Ground Radar Model
Kaasalainen, et al (2002) Ostro et al.(2004)
Lessons Learned from Hayabusa (3):
Prepare for Many Rehearsals
24

25. Lessons Learned from Hayabusa (4):
Build the Best Team in the World
and A Leader Must Understand True Followership
Thank You!
25