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Home , Akatsuki (spacecraft), Hayabusa, Hayabusa2, IKAROS, MINERVA (spacecraft)

Hayabusa2 Sample Return Mission

H. Kuninaka JSPEC/JAXA 10th SBAG Target Asteroid : 1999 JU3

Orbit Itokawa Rotation period: 0.3178day (~7.6 h) ����)�(331, 20), (73, -62) Kawakami Model Mueller Model

Axis ratio = 1.3 : 1.1 : 1.0

Size : 0.87 ± 0.03 km Albedo : 0.070 ± 0.006 H=18.82 ± 0.021, G=0.110 ± 0.007 Type : Cg

(by Mueller 2 Shape model by Kawakami et. al) vs (1) Hayabusa Hayabusa2

Size � 1m�1.6m�1.1� Size � 1m�1.6m�1.25��body� �body� Mass� 600kg�Wet� Mass� 510kg�Wet� �

� � �

� Communication : X-band + Ka-band � engine : modified � Small : MASCOT(Mobile Asteroid Surface Scout� from DLR � AOCS : 4 reaction wheels  Nominal Payloads for Science Payloads Specifications Multiband Imager Wavelength: 0.4 – 1.0 µm, FOV: 5.7 deg x 5.7 deg, Pixel Number: 1024 (ONC-T) x 1024 px filter (ul, b, v, w, x, p, Wide) (Heritage of Hayabusa) Near IR Spectrometer Wavelength: 1.8 – 3.2 µm, FOV: 0.1 deg x 0.1 deg (NIRS3) (Heritage of Hayabusa, but 3µm range is new) Thermal IR Imager Wavelength: 8 – 12 µm, FOV: 12 deg x 16 deg, Pixel Number: 320 x 240 (TIR) px (Heritage of ) Laser Altimeter () Measurement Range: 30 m – 25 km (Heritage of Hayabusa) Sampler Minor modifications from Hayabusa-1 (Heritage of Hayabusa) Small Carry-on Impactor Small system released form the spacecraft to form an artificial crater on (SCI) the surface (New) Separation Camera Small, detached camera to watch operation of Small Carry-on Impactor (DCAM) (Heritage of Ikaros) Small Rover Similar to MINERVA of Hayabusa-1 (MINERVA II-1, II-2) (possible payload: Cameras, ) (Heritage of Hayabusa) Small Rover Supplied from DLR & CNES (MASCOT) MicrOmega, MAG, CAM, MARA 4 Hayabusa2 Mission Schedule year 2014 2015 2016 2017 2018 2019 2020

month � � 12 06 12 06 08 12 12

Spacecraft IES operation

Launch windows Earth Swing-by Departure Earth Arrival at Science from 1999 return 1999JU3 observation JU3 , Sampling IES operation Impactor

5 Mission Outline of Hayabusa-2

Launch June 2018 : Arrival at 1999 JU3 Global observation of the asteroid, Dec 2014 deployment of small rover/lander, Mothership carries multiple samplings an impactor. Sample analysis New Experiment

Earth Return Dec. 2020

Dec. 2019 : Departure

2019 The impactor collides to the surface of the asteroid. Further exploration 6 Potential International Cooperation

JAPAN USA * To NASA To JAXA •US scientists participation •Deep Space Network support •Asteroid sample provision •Radiometric navigation support •Accommodation of appointed •Cooperation with OSIRIS-REx personnel on mission ops.

Europe

*NASA/JAXA LOA on potential collaboration between the Hayabusa-2 and OSIRIS-REx missions, Nov. 9, 2012

Summary Hayabusa2 in under development.

SOE of Hayabusa2 Launch at end of 2014 Proximity Operation from June 2018 to Dec. 2019 Earth Return on Dec. 2020

Hayabusa and Hayabusa2 will contribute to Human NEA Mission Optical Navigation in approch to asteroid from heliocentric space Landmark Navigation in proximity operation around asteroid Autolanding in zero gravity field Redundancy against malfunctions in long flight Information and Knowledge on C and S-type 9 Back-up Assembly (ITA)

Thruster 4 units including 1 stand-by 3 units simultaneous operation System thrust 5 - 30 mN System Power 250 – 1,200 W Specific Imp. 2,600 – 3,000 sec Ion Prod. Cost < 250 eV Lifetime > 18,000 hours Gimbal +/-5 deg Xe loading < 73 kg Dry weight < 70 kg Impactor � high speed debris � high speed ejecta � low speed ejecta separation explosion � Separation mechanism

� Impactor

� 1999 JU3

� ��� 12 Impactor experiment half size case

explosion

trajectory

13 impact!