Hayabusa2 !
Asteroid Sample Return Mission!
!
!
!
!
!
!
!
!
!
!
!
!
!H. Kuninaka!
!
!
!
!
!
!JSPEC/JAXA!
Mission Outline of Hayabusa-2
Launch
June 2018 : Arrival at 1999 JU3
Global observation of the asteroid,
deployment of small rover/lander,
multiple samplings
Dec 2014
Mothership carries
an impactor.
New Experiment
Sample analysis
Earth Return
Dec. 2020
Dec. 2019 : Departure
2019
The impactor collides to the
surface of the asteroid.
Further exploration
2
Target Asteroid : 1999 JU3
Rotation period: 0.3178day (~7.6 h)
Orbit
Itokawa�
（λ，β)＝(331, 20), (73, -62)
Kawakami Model
Mueller Model�
Axis ratio = 1.3 : 1.1 : 1.0
Size : 0.87 ± 0.03 km
Mars
Earth
Albedo : 0.070 ± 0.006
H=18.82 ± 0.021, G=0.110 ± 0.007
Type : Cg
Shape model by Kawakami
(by Mueller
3
et. al)
イオンエンジン Ion Engine 推進系スラスタ（12基） RCS Thrusters (12)
光学航法カメラ-­‐ 望遠、広角 (ONC-­‐T, ONC-­‐W1) Op6cal Naviga6on Camera-­‐Telephoto & Wide)
DLR/CNES開発の着陸機
(MASCOT) Lander by DLR
ローバ(MINERVA-­‐II) Rovers
中間赤外カメラ(TIR)
Thermal Infrared Imager
衝突装置 (SCI)
Small Carry-­‐on Impactor
ターゲットマーカ（5基） Target Markers (5)
分離カメラ(DCAM3)
Deployable Camera
Xバンド高利得アンテナ X Band High Gain Antenna Ｘバンド低利得ｱﾝﾃﾅ X Band Low Gain Antenna Ｘバンド中利得ｱﾝﾃﾅ 太陽電池パネル X Band Middle Gain Antenna Solar Array Panel
Kaバンド高利得ｱﾝﾃﾅ Ka Band　High Gain Antenna
スタートラッカ
Star Trackers
近赤外分光計(NIRS3)
Near Infrared Spectrometer
再突入カプセル Reentry Capsule
サンプラホーン Sampler Horn
レーザ高度計（LIDAR） Laser Al6meter
光学航法カメラ-­‐広角(ONC-­‐W2) 6�
Op6cal Naviga6on Camera-­‐Wide
Major Improvements in Hayabusa2�
Attitude and Orbit Control System (AOCS)
Reaction wheels : 3 à 4
Propulsion System (RCS)
Routing of the pipes of the fuel and oxidizer
Ion Engine System (IES)
Thrust : 8mN à 10mN
Neutralizer: Longer life time
Target Marker (TM)
3 à 5�
7
Changes of Mission Payloads of Hayabusa2�
Optical Navigation Camera (ONC)
filter set was changed
(ONC-T : 6.35deg^2, ONC-W : 65.24deg^2)
Light Detection and Ranging (LIDAR)
adapted to low albedo of C-type
(Range : 30m – 25km)
Near Infrared Spectrometer (NIRS3)
absorption by H2O
Wave length : 0.85m – 2.10µm à 1.8 – 3.2 µm
Thermal Infrared Imager (TIR) – New
Thermal radiation
Wave length : 8 – 12 µm�
8
Small Lander and Rovers
MASCOT�
by DLR and CNES�
MINERVA-II�
MASCOT�
-II-2�
-II-1�
by Tohoku Univ. &
MINERVA-II consortium�
MINERVA-II-1�
MINERVA-II-2�
-1A�
by JAXA MINERVA-II Team�
-1B�
9
New Payloads of Hayabusa2�
Ka-HGA
X-LGA-A
X-HGA
High Gain Antenna (HGA)
X-band 8GHz
Ka-band 32GHz -- New�
X-MGA
X-LGA-B
X-LGA-C
SCI
Small Carry-on Impactor (SCI)
+ Deployable Camera (DCAM3)
 
 
 
 
Shape of projectile: Shell type.
Deformation process: < 0.5ms
Velocity of projectile: > 2000m/s.
Weight of formed projectile: > 2kg.
Mass of projectile
Small Carry-on impactor of HAYABUSA-2 Mission (IAC-11.A3.4.6)
DCOM3�
Velocity of projectile
Observation : by DCOM3
10
Deformation of liner
!
!
!
!
Make a small crater on the surface:
2kg cupper liner
2km/s
Artificial Crater Generation Operation�
separation
explosion
(a)
①SCI Separation
②Horizontal Escape
③Vertical Escape
(b)
Impact
Observation�
Detonation &
Impact�
1999 JU3�
(a) high speed debris
(b) high speed ejecta
(c) low speed ejecta
(c)
U
1999J
④DCAM3
Separation
3�
⑤Detonation
& Impact
⑥Return to HP
11
はやぶさ２　2014年打ち上げ、2018年着、2020年帰還�
Hayabusa2 Mission Schedule
year
2014
month
�
� 12
Spacecraft�
Launch windows�
2015
2016
2017
2018
06
06 12
2019
08
2020
12
12
IES operation�
Earth Swing-by
Arrival at Science
1999JU3� observation,
Sampling�
Departure
from 1999
JU3�
Earth
return�
IES operation�
Impactor�
23